286 results about "Satellite bus" patented technology

The invention discloses a morning orbit computing power satellite, and belongs to the field of aerospace technology and space infrastructure. The satellite comprises a satellite platform and a computing force load arranged on the satellite platform. The satellite platform is provided with a condensation type energy system and a space pump drive fluid loop system. The condensation type energy system adopts an expandable condensation type solar cell array to generate power, switches a power supply mode according to an illumination period and an earth shadow period of a morning and night orbit, and supplies power to computing force loads and platform equipment. The space pump drive fluid loop system adopts an expandable flexible radiation cooling plate for heat dissipation, heat dissipation is conducted on computing force loads through a fluid loop, and a heating assembly is arranged to prevent a working medium from being frozen under the low-temperature working condition. Through the expandable structure and the orbit environment adaptability design, continuous energy supply and effective heat management are provided for the computing power load in the morning and night orbit environment, and high-power-consumption computing power load in-orbit stable operation is supported.

The invention belongs to the technical field of space remote sensing surveying and mapping, and particularly relates to a monitoring system and method for a front and rear view visual axis included angle and absolute direction of a surveying and mapping camera. The method comprises the following steps: S1, through side sway of a satellite platform, taking a time for sky imaging calibration as a reference time; s2, calculating a rotation matrix from a front and rear view ground camera measurement coordinate system to a star camera coordinate system at a reference moment; s3, calculating respective thermal deformation matrixes of the star camera coordinate system, the front-view camera measurement coordinate system and the rear-view camera measurement coordinate system; s4, obtaining a real-time rotation matrix from the measurement coordinate system of the front-view camera to the coordinate system of the star camera and a real-time rotation matrix from the measurement coordinate system of the rear-view camera to the coordinate system of the star camera at the measurement moment; and S5, carrying out arc cosine calculation on the two absolute pointing vectors to obtain a visual axis included angle between the front-view camera and the rear-view camera at the measurement moment. According to the invention, while the geometric accuracy of the surveying and mapping camera is ensured, the real-time performance of measurement and the comprehensiveness of subsystem monitoring are realized at the same time.

The invention discloses a super-large plane array type space computing power center, and belongs to the field of space technologies and space infrastructures. The space computing power center is deployed in a morning and evening orbit and comprises a plurality of computing power satellites which are physically docked in orbit through a docking mechanism. Each computing power satellite comprises a satellite platform, and a computing power load, a condensation type energy system and a space pump drive fluid loop system which are arranged on the satellite platform, and a docking mechanism for inter-satellite in-orbit physical docking is also assembled on the satellite platform. A plurality of computing power satellites form a planar array type rigid whole body through the docking mechanism, and energy scheduling among the light condensation type energy systems is realized based on the docking mechanism. According to the space computing power center, through multi-satellite physical docking and energy collaborative scheduling, the energy utilization efficiency and the power supply reliability of the system are improved.

The invention discloses a satellite-borne SAR (Synthetic Aperture Radar) radar target real-time guiding method based on ADS-B (Automatic Dependent Surveillance-Broadcast) signals, which relates to the technical field of radar control, and comprises the following steps: receiving Beidou dual-band signals and global ADS-B signals in real time, resolving by adopting a carrier phase double-difference ionosphere elimination combinatorial algorithm, and obtaining a satellite-borne SAR generating satellite platform pose data including satellite position component data, satellite speed component data and satellite attitude component data; inputting the airspace target point cloud data set into an adaptive airspace clustering algorithm, dynamically adjusting a clustering neighborhood radius by using satellite speed component data, and outputting central geographic coordinates of a target dense area; fusing the beam pointing vector and the angular velocity data through a beam-attitude dynamic coupling controller, and generating a phase shifter code value adjustment instruction; the neighborhood recognition range is dynamically adjusted through the real-time motion state of the satellite, and the positioning precision and timeliness of the dynamic airspace target dense area are remarkably improved. And the continuous monitoring capability and the guiding precision of the time-sensitive target are improved.

The invention discloses an antenna layout method for a communication satellite. The antenna layout method comprises the following steps: S1, determining directions of antennas in an unfolded state and a spatial relationship between the antennas; s2, adjusting the relationship between the assembly and the satellite platform, and ensuring that the field of view of the antenna is not shielded in an unfolded state; s3, the relation between the antennas and the satellite platform in the folded state is adjusted, and it is guaranteed that no interference exists between the antennas and between the antennas and the satellite platform in the folded state; s4, solving a rotation axis unit vector and a rotation angle of the antenna; if the first constraint judgment condition is not met, returning to the step 2; if yes, executing the step 5, and rotating according to the rotating shaft unit vector and the rotating angle to obtain a corrected layout position; 6, if the second constraint judgment condition is not met, returning to the step 2; and if yes, outputting a result. According to the method provided by the invention, the antenna layout which meets the use requirements of an antenna system, the internal space envelope of a fairing and the size limitation of a satellite platform can be obtained.

The invention discloses a satellite-borne space-based measurement and control method based on a non-ground network and related equipment. The method is used for a satellite-borne space-based measurement and control device, the satellite-borne space-based measurement and control device is arranged on a low-orbit satellite platform, and the method comprises the following steps: respectively obtaining real-time orbit parameters of a low-orbit satellite, GNSS positioning information and a pre-stored high-orbit satellite coverage information table; based on the current orbit parameter, the GNSS positioning information and a high-orbit satellite coverage information table of a high-orbit satellite pre-stored or periodically updated from a satellite service computer, calculating a space-time relationship between the low-orbit satellite and a cell coverage range; and under the condition that it is predicted and determined that the cell coverage of the target high-orbit satellite is about to enter according to the time-space relationship obtained through calculation, waking up in advance and initiating cell search and a control flow of accessing at any time. The problems that an existing space-based measurement and control technology is high in construction cost, limited in multiple access capacity and poor in dynamic adaptability can be solved.

An integrated spaceborne SAR satellite platform, belonging to the field of spacecraft technology, solves the problems of poor temperature uniformity of existing satellite platform mounting plates, large SAR antenna envelope, inability to meet high-precision single-unit installation requirements, and low structural strength. The platform comprises: a SAR antenna, a feed assembly, a single-unit mounting plate, an external single-unit device, an internal single-unit device, a platform main frame, and a solar sail; the platform main frame, single-unit mounting plate, and solar sail constitute the cabin; the solar sail is located below the platform main frame; the SAR antenna, feed assembly, and external single-unit device are mounted on the outer surface of the single-unit mounting plate; the internal single-unit device is mounted on the inner surface of the single-unit mounting plate; the single-unit mounting plate includes a honeycomb panel, metal gaskets, and pre-embedded heat pipes; the honeycomb panel includes a honeycomb core and a honeycomb panel skin; the metal gaskets are connected to the pre-embedded heat pipes. This invention is applicable to satellite platform spacecraft platforms, spacecraft configuration and layout design, spacecraft structural thermal control design, spacecraft on-orbit monitoring, and SAR satellite on-orbit active compensation.

The invention relates to the technical field of satellites, in particular to a three-super platform actuator eddy current sensor fault autonomous reconstruction method. Comprising the following steps: according to a parallel mechanism kinematics relationship of each actuator, determining a first relationship between axial displacement measured by an actuator eddy current sensor and a load relative to a six-degree-of-freedom pose of a satellite platform; determining a parallel mechanism kinematics relationship of the fault-free eddy current sensor, and determining a second relationship between the axial displacement and the load measured by the fault-free eddy current sensor and the six-degree-of-freedom pose of the satellite platform; according to the first relation and the second relation, matrix reconstruction is carried out on the remaining fault-free actuator eddy current sensors, and an autonomous reconstruction matrix is obtained; and according to the autonomous reconstruction matrix and the measurement of the fault-free actuator eddy current sensor, obtaining all actuator eddy current measurement values of the actuator where the fault eddy current sensor is located. According to the method, when the eddy current sensor has a fault, the eddy current sensor distribution array is reconstructed, and three-super control is recovered.

The invention belongs to the technical field of spaceflight on-orbit services, and particularly relates to a complex environment target recognition approaching method based on dual-band imaging under a satellite platform, which is based on three common sensors, namely an infrared camera, a visible light camera and a laser range finder, and is characterized in that an image information source adopts infrared and visible light multi-spectrum fusion; software time synchronization and an image registration mode are introduced into a synchronization mode, infrared fast mean value judgment suitable for on-satellite embedding is introduced, an earth background suppression technology and a target information enhancement scheme are added, fusion tracking and ranging cooperation of vision and a laser range finder is adopted, and meanwhile, a laser range finder start-stop strategy is designed according to on-satellite power consumption. According to the invention, the defect of insufficient robustness of a single sensor facing an earth complex background observation target in the view field change process of a satellite platform is overcome.

According to the capturing and tracking integrated space laser communication terminal and the inter-satellite laser communication method, a capturing mechanism and a tracking mechanism of the laser communication terminal adopt the same mechanism assembly, when capturing and link building are carried out in orbit, a large-stroke fast reflecting mirror is used for carrying out directional scanning, and after an opposite satellite laser communication terminal receives a light beam of the satellite laser communication terminal of the opposite party, the capturing and tracking are carried out; the laser communication terminals of the two parties immediately switch to fine tracking link establishment; and if the satellite position of the opposite side exceeds the scanning range of the satellite laser communication terminal of the local side, pre-pointing and angle unloading correction are carried out by using a satellite platform of the local side. The design that receiving communication light and transmitting communication light of receiving and transmitting optics of the laser communication terminal share one optical assembly is simple and reliable, a large divergence angle is adopted, a large scanning area is achieved, the capturing time is shortened, and the capturing probability is improved. According to the invention, a capturing and tracking integrated design scheme is adopted, so that the system complexity, weight, size and power consumption of the laser communication terminal are reduced.

A relay satellite platform communication device for space-ground networking belongs to the field of relay satellites, and is formed by system-level integration of four core technologies including a structure-electrical integrated central bearing frame, an integrated three-surface pluggable modular system, a conformal antenna integrated multifunctional shell and an internal and external cooperative heat pipe heat dissipation network. A framework-module-skin three-layer deep coupling system framework is constructed, six faces of a center bearing structure are divided into a movable area and a static area, the movable area is used for achieving function reconfiguration and on-orbit maintenance, and the static area is used for deploying a high-reliability platform foundation system which is fixed once launched. According to the invention, the problems of difficulty in on-orbit maintenance, low reliability and efficiency bottleneck caused by discrete architecture and functional coupling of a traditional relay satellite are solved, and a high-reliability, high-flexibility and easy-to-maintain satellite platform foundation is provided for constructing a dynamic reconfigurable space-ground integrated information network.

The invention discloses a satellite integrated electronic system. According to the system, a heterogeneous FPGA architecture is adopted, a satellite service management module is deployed on a first FPGA chip, and a measurement and control module and an encryption and decryption module are integrated on a second FPGA chip. The system realizes fault isolation through the design of an independent power domain and a reset domain of the measurement and control and encryption and decryption module, ensures that a measurement and control link is not interrupted through a hardware bypass channel in the second FPGA chip, and improves the reliability of the system. The encryption and decryption module adopts an encryption mode mapping graph and management system, supports a dynamic key management mechanism triggered based on three events of periodic switching, mapping graph updating and periodic parameter updating, can flexibly configure an encryption strategy according to an on-orbit task demand, and improves the security and adaptability of the system. The problems that in the prior art, chip performance and cost are difficult to balance, the integration level is low, and a whole machine fails due to a single-point fault are effectively solved, and the method is particularly suitable for a microsatellite platform with strict requirements for cost, size and reliability.

The application discloses a general service method and system applied to a satellite platform and belongs to the field of remote sensing / communication satellite platforms, and solves the technical problems that in the prior art, due to the need of new load access for new adaptability development and test work, a long development cycle is caused, and under the condition that test is not comprehensive, there is a risk of load service failure, and maintenance is difficult. Step 1, a general service template table is constructed; step 2, after the general service template table is filled in, the general service template table is converted into satellite on-service instructions; and step 3, a general service program is designed and is used for executing the satellite on-service instructions. The application is used for realizing the general service method without special customization development for different loads.

The application provides a satellite-borne multi-viewing-angle polarization spectrum imaging system for aerosol optical parameter measurement, and belongs to the technical field of optical imaging. The system is loaded on a satellite platform and comprises a telescope objective, a multi-slit assembly, a light-splitting prism, a collimating lens group, a plane grating group, an imaging lens group, a depolarization light-splitting prism group, a polaroid group and a detector group. The system is based on static multi-viewing-angle synchronous observation design, and realizes high-precision detection of aerosol optical parameters through multi-viewing-angle, hyperspectral and full-polarization multi-dimensional information fusion.

The application provides a small satellite platform structure which carries a large amount of propellant and is connected and separated in point mode, belongs to the technical field of spacecraft structure, and comprises a frame, a bottom plate, a lower cabin partition plate, a storage tank support rod, a middle layer plate, an upper cabin partition plate, a top plate and a side plate, so that the side plate surrounds the parallelly arranged bottom plate, middle layer plate and top plate into a closed box body, the bottom plate is connected to the frame, the storage tanks are arranged diagonally in the round holes on the bottom plate and the middle layer plate, and the storage tank support rods are uniformly distributed around the round holes; the middle layer plate separates the box body into an upper cabin and a lower cabin, the upper cabin partition plate is connected in the upper cabin, and the lower cabin partition plate is connected in the lower cabin. The application proposes a configuration of "point connection + storage tank sinking", meets the demand of the small satellite platform for carrying a large amount of propellant, effectively reduces the whole satellite center of mass, and improves the satellite dynamic environment; meanwhile, the bottom main load-bearing frame cooperates with a detachable adapter block, can adapt to different mechanical interfaces of launch vehicles, and realizes point connection and separation.

The application discloses a space remote sensing scanning imaging system self-rotation eliminating turntable mechanism and a construction method thereof, and belongs to the technical field of space remote sensing. The mechanism comprises a first self-rotation eliminating mechanism and a second self-rotation eliminating mechanism, the first self-rotation eliminating mechanism and the second self-rotation eliminating mechanism are respectively used for driving the scanning movement and the swing of the space remote sensing scanning imaging system; the first self-rotation eliminating mechanism is connected with a satellite platform, and the second self-rotation eliminating mechanism is connected with the space remote sensing scanning imaging system; the first self-rotation eliminating mechanism comprises a first double-output-shaft motor, which is used for driving the coaxial reverse movement of the connected space remote sensing scanning imaging system and a first rotation eliminating device; the second self-rotation eliminating mechanism comprises a second double-output-shaft motor, which is used for driving the coaxial reverse movement of the connected space remote sensing scanning imaging system and a second rotation eliminating device. When the space remote sensing scanning imaging system is in scanning movement and swing, the satellite is provided with equal and opposite angular momentum, so as to offset the disturbance brought to the satellite by the movement of the space remote sensing scanning imaging system, and the satellite keeps a stable attitude.

The invention discloses a SysML-based satellite constellation architecture modeling method and system and a storage medium, and the method comprises the steps: analyzing a satellite constellation system strategy scene and a target described by a natural language, and building a satellite constellation architecture system layer model by using a SysML language; based on a system capability demand model in the constructed system layer model, building the system layer model by combining an RFLP (Restriction Fragment Length Polymorphism) method and a SysML (Systematic Modeling Language); analyzing designed functions in the constructed system layer model through a system forward design method, and respectively establishing a satellite platform model and a satellite load model by using an RFLP (Restriction Fragment Length Polymorphism) method and an SysML (SysML) modeling language; and extracting parameters from the constructed satellite parameter model, platform parameter model and load parameter model to carry out orbit design, and establishing a satellite orbit model by using an SysML language. According to the method, comprehensive and visual modeling of the satellite constellation from a macroscopic system to a microcosmic component is realized, the standardization, consistency and understandability of the model are greatly improved, and the modeling efficiency is improved.

The invention discloses a data error control method and system for high-speed data transmission of a camera, and relates to the technical field of satellite communication. The method comprises the following steps: quantitatively evaluating the state of a communication link based on the camera data throughput and the effective data receiving rate of a satellite-borne bus, and dynamically adjusting the working mode of the communication link based on the state of the communication link so as to ensure the stability of the data transmission process; dynamic credibility marking is carried out on the camera data based on the satellite-borne bus data error rate, and abnormal camera data can be accurately identified; and carrying out secondary state marking on the camera data marked by the credibility based on the state parameters of the processor. Dynamic intelligent fault-tolerant control over the mass high-speed data flow of the satellite-borne camera in the transmission process is achieved, and the integrity and reliability of data under bandwidth pressure and space interference are effectively guaranteed.

The invention provides a control method of a panel satellite large-size flexible solar wing driving device. The driving device comprises a satellite body, a double-shaft SADA, a swing rod, a hinge, a pressing and releasing mechanism and an ROSA solar wing. The control method comprises the steps that a release signal is sent to the pressing and releasing mechanism, the pressing and releasing mechanism releases the pressed solar wing after receiving the release signal, and the solar wing is driven by a hinge at one end of a swing rod to be passively unfolded by a first angle; according to the target angle and the first angle, calculating a second angle that the double-shaft SADA needs to rotate; a rotation signal is sent to the double-shaft SADA, the double-shaft SADA drives the solar wing to continue to rotate by a second angle after receiving the rotation signal, and a rotation in-place signal is sent out; and an unfolding signal is sent to the solar wing, and the solar wing starts to unfold the cell array plane until the cell array plane is completely unfolded. The control method improves the energy utilization efficiency of the whole satellite platform.

The invention discloses a biomedicine standardized cubesat platform and a working method, and relates to the technical field of space.The biomedicine standardized cubesat platform adopts a 3U cubesat framework, the top layer of the 3U cubesat framework is provided with a satellite bus module, the middle layer of the 3U cubesat framework is provided with an energy and environmental control life support module, and the bottom layer of the 3U cubesat framework is provided with a biological experiment module; the satellite bus module is in bidirectional communication with the energy and environment control life support module and the biological experiment module through data interfaces. The satellite bus module further communicates with a ground station; the energy and environment control and life support module supplies energy to the satellite bus module and the biological experiment module through electrical interfaces, and provides oxygen supply, water supply and environment regulation and control support for the biological experiment module through a fluid transmission channel. Through a standardized and modularized cubesat structure, the functions of biological sample culture, environment regulation and control, real-time monitoring, data return and the like are integrated, and a low-cost and quick-response technical support is provided for space life science experiments.

The invention provides a high strabismus imaging method and system for cooperative scanning of an agile attitude and a load. The method comprises the following steps: calculating optimal imaging parameters of a high strabismus mode; establishing a load high-squint stripe imaging method under satellite level flight and left and right side-looking attitudes; establishing an SAR imaging coordinate system in a posture and load cooperative scanning state; establishing an attitude agile maneuvering and load electric scanning coordinated slip aggregation mode implementation method; and establishing an azimuth large squint multi-target mode observation mode. According to the invention, the agile maneuvering capability of the satellite platform and the large-angle scanning capability of the load phased-array antenna are fully utilized, and the agile maneuvering capability of the satellite platform and the large-angle scanning capability of the load phased-array antenna cooperate to realize in-orbit large-squint imaging, so that the method has popularization and practical values for improving the in-orbit application efficiency of light and small

The application discloses a kind of distributed space-based radar networking tracking methods based on message passing, based on the distributed space-based radar networking of multiple satellite platforms, antenna array, transmitting system, receiving system, radar power etc., the method comprises: the sequence of first target motion state, target visible state, data association and latent variable in joint observation variable are described using factor graph;Based on the connection relationship of variable node and factor node in factor graph, the approximate solution of joint posterior probability density is solved using BP-MF combined approximation method;According to the approximate solution of joint probability density, the target is tracked.The present application is based on the distributed space-based radar networking, combines factor graph and uses BP-MF combined approximation method to convert the solution of high-dimensional posterior probability density fitting into the solution of low-dimensional posterior probability density product, solves the problem of cumulative propagation of estimation error and identification risk in the case of guaranteeing networking performance using distributed networking tracking method, avoids.

The application relates to an on-orbit maintenance method for a self-repairable satellite-borne DSP, which is realized by an on-orbit maintenance system and is used for maintaining and managing a DSP chip; the on-orbit maintenance method comprises the following steps: S1, powering on the on-orbit maintenance system; S2, performing three-mode redundancy comparison error correction and CRC check word checking to judge whether the checking is passed; S3, mapping the DSP chip to a target chip area address and performing DSP program data loading; S4, judging whether the monitoring function of the DSP chip is normal; and S5, downloading the chip area address of the DSP program data which is not passed in the telemetry and executing satellite platform instructions to repair the DSP program data. The application has simple architecture, low implementation difficulty, can effectively prolong the on-orbit life of a satellite and other space vehicles while keeping low cost.

This invention relates to a method for inverting remote sensing data from overlapping strong and weak absorption lines of greenhouse gases, belonging to the field of satellite remote sensing technology. Specifically, it includes the following steps: Step 1: Constructing an optical system, including a satellite platform, camera 1, and camera 2; camera 1 and camera 2 are mounted at the bottom of the satellite platform; camera 1 and camera 2 are mirrored; the imaging spectral band of camera 1 moves from the weak absorption spectral band to the strong absorption spectral band along the positive push-broom direction to the negative push-broom direction; the imaging spectral band of camera 2 is in the opposite direction; the optical system moves horizontally from left to right to achieve horizontal push-brooming of greenhouse gases on the ground, obtaining a dual-camera fused image; the dual-camera differential absorption spectroscopy algorithm is used to invert the dual-camera fused image to obtain the greenhouse gas column concentration; this invention, based on the spectral characteristics of strong and weak absorption lines of greenhouse gases, adopts a detector focal plane segmentation method, and the dual cameras achieve differential absorption and inversion in the same region, which can guide the design of greenhouse gas detection micro / nano satellite payloads.

The invention provides a satellite-borne product installation precision testing device and method. The satellite-borne product installation precision testing device comprises a single-machine product, a reference mirror LJ1 assembly, a satellite platform and a reference mirror LJ2 assembly. According to the invention, the assembly precision test of the satellite product is realized through a high-precision measurement system, and the assembly precision is rapidly calculated, and the adjustment direction and the adjustment amount are directly given in an Euler rotation angle mode, so that rapid calculation and accurate orientation adjustment are realized; a reference mirror is used as a measurement basis, an electronic theodolite is used as test equipment, industrial measurement software (SA) is matched for use, and the size requirement and the use method of the reference mirror are provided. The method has the advantages that the error rate of testing and adjusting is effectively avoided, and the method is simple, easy to understand and high in operation adaptability; the device is suitable for assembly precision test and adjustment of all aerospace products.

The invention relates to a satellite capturing and locking device, and belongs to the field of satellite docking. The satellite capturing and locking device comprises an active end and a passive end, the driving end comprises a driving end base, a guide mechanism, a driving mechanism and two locking mechanisms; the guide mechanism comprises a guide frame and a guide plate; the guide plate is in an inverted cone shape; the passive end comprises a passive end base and a caught rod; the guide plate is used for guiding the captured rod into the opening; the driving mechanism is used for driving the two locking mechanisms to move oppositely so as to clamp the captured rod, and therefore locking between the driven end and the driving end is achieved. The caught rod at the driven end is clamped left and right through the two locking mechanisms to achieve locking, the two locking mechanisms are arranged in a bilateral symmetry mode, namely, the two locking mechanisms are arranged at intervals in the transverse direction, the axial distance between two satellites after locking is reduced, and therefore the size of a satellite platform is reduced. The locking mechanism comprises a first-stage locking unit and a second-stage locking unit, and the ejection speed during separation can be guaranteed.

This invention relates to a lightweight, miniaturized 3S configuration triaxial integrated fiber-MEMS inertial measurement unit, belonging to the field of measurement devices. It includes a base cover, a power supply and detection board assembly located on the top of the base cover, a light source assembly located above the power supply and detection board assembly, a MEMS assembly mounted above the light source assembly, a base fixed to the base cover, fiber optic ring assemblies fixed to the base, and a reference mirror fixed to the top of the base. The power supply and detection board assembly, the light source assembly, and the MEMS assembly are all arranged inside the base. The three fiber optic ring assemblies are evenly distributed on a conical surface with an outer half-cone angle of 54.74° and a bottom projection of 120°. The light source assembly shares a light source with the three fiber optic ring assemblies via a 1*3 coupler. This invention eliminates the unnecessary space occupied by the traditional three independent light source configuration, reduces the overall volume, and improves optical path consistency and system stability. It can meet the engineering requirements of commercial satellite platforms for the miniaturization and mass production of inertial measurement components.

A first satellite includes a first host-side bridge and a first host, connected with a network via the first host-side bridge, mounted thereon. A second satellite includes a first I / O-side bridge and a first I / O device, connected with the network via the first I / O-side bridge, mounted thereon. A management device selects the first host mounted on at least one of the first satellites and the first I / O device mounted on at least one of the second satellites, according to a configuration request, and forms an information processing device in which the first host-side bridge connected with the selected first host and the first I / O-side bridge connected with the selected first I / O device constitute a virtual computer internal bus.

The application discloses a kind of integrated space laser communication terminal and inter-satellite laser communication method, the acquisition mechanism and tracking mechanism of this laser communication terminal use same mechanism component, when carrying out acquisition in orbit and link establishment, utilize large-stroke fast mirror to carry out pointing scanning, after the laser communication terminal of opposite satellite receives the light beam of the laser communication terminal of this side, both sides laser communication terminal enters precision tracking link establishment immediately;If the position of opposite satellite exceeds the scanning range of the laser communication terminal of this side, utilize the pre-pointing and angle unloading correction of the platform of this side.The design of laser communication terminal transceiving optics, receiving communication light and transmitting communication light share an optical assembly, simple and reliable, large divergence angle is used to realize larger scanning area, reduce acquisition time and improve acquisition probability.The application uses integrated acquisition and tracking design scheme, reduces the system complexity, weight, size and power consumption of laser communication terminal.

The invention relates to a connecting rod driving unfolding mechanism for a large-scale deployable array plane antenna, and belongs to the technical field of spaceborne antennas. Comprising two antenna multi-layer array surface structures, a satellite platform and two groups of driving unfolding assemblies, wherein the satellite platform is horizontally placed; the two antenna multi-layer array surface structures are arranged below the satellite platform in a vertical folded state; the two driving unfolding assemblies are symmetrically arranged on the front side wall and the rear side wall of the satellite platform. Each driving unfolding assembly comprises a fixed truss, two short connecting rods, two long connecting rods, two synchronous tooth holders, a driving synchronous belt, two follow-up synchronous belts, ten belt wheels and inter-plate hinges. Power is provided for the two antenna multi-layer array surface structures to be changed from a completely folded state to an unfolded state through the two groups of driving unfolding assemblies, and the unfolding speed of the antenna multi-layer array surface structures is controlled; the connecting rod driving unfolding mechanism for the large-scale deployable array plane antenna provides unfolding power and unfolding rigidity for the antenna, and has the characteristics of high storage ratio, high rigidity, high precision and controllable unfolding.