1469 results about "Spaceflight" patented technology

Systems and methods for providing a space launch service platform (SLSP) that integrates artificial intelligence and data analytics to support launch operations. The SLSP may connect to multiple data sources, collect data, and standardize the collected data according to regulatory and operational standards. The SLSP may evaluate launch safety and risks using standardized data and generate a situational analysis for decision-making. The SLSP may provide graphical overlays and decision-support tools to highlight optimal launch windows and potential risks.

The invention discloses a multi-satellite cooperative distributed game control method and device, a computer program and a storage medium, belongs to the technical field of spaceflight, and particularly relates to a satellite attitude control and game control method. The problem that in the prior art, resolving of the overall control quantity depends on a center unit, and constraint processing on the size of the microsatellite control torque is not accurate enough is solved. The method comprises the following steps: S1, according to attitude dynamics modeling and pseudo-linearization processing of the combined spacecraft, obtaining a state dependence coefficient model; s2, obtaining a local optimal control strategy of each satellite in the combined spacecraft through a model prediction control method according to the state dependence coefficient model in combination with a dynamic model in a prediction time domain and flywheel constraint conditions; and S3, obtaining a distributed Nash equilibrium solution through a distributed iteration and global coordination method according to the local optimal control strategy of each satellite in combination with communication topology information. The method is suitable for efficient cooperation tasks of large-scale satellite groups and microsatellite systems.

The invention discloses a complex aerospace product man-machine cooperation assembly-oriented body-equipped agent packaging method and device. The method comprises the following steps: a sensing layer realizes multi-modal intention and environment sensing by using a large language model; the reasoning layer analyzes a structured assembly plan sequence through an assembly scene map; and the execution layer converts the target coordinate into a rotation angle to generate an action code. According to the method, the assembly plan sequence is generated according to the sensing result and is automatically converted into the robot execution code through the combination of the body agent packaging and the large language model, so that the self-adaptive capability of the man-machine cooperative assembly process is improved; therefore, the problems of high system integration difficulty, insufficient task adaptability and high-efficiency cooperation difficulty in man-machine cooperation assembly of complex aerospace products are solved.

The invention belongs to the technical field of aerospace engineering, and discloses a flexible radiator which comprises a radiation assembly, the radiation assembly comprises a plurality of radiation plates which are rotationally connected in sequence, each radiation plate comprises a liquid cooling pipe set and a radiation film arranged on the liquid cooling pipe set, and cooling liquid circulates in the liquid cooling pipe set. The material density is low, the structural mass is effectively reduced, a plurality of radiant panels are rotationally connected in sequence, the radiant panels are in a folded state during emission, then a radiator with enough radiation area can be emitted under the condition that the size of a spacecraft is limited, and the heat dissipation requirement of high-power electronic equipment is met.

The invention discloses a method for reducing the inclusion degree of metal particles in additive manufacturing of a spaceflight propulsion chamber. The method comprises the following steps that 1, a printing layer data set is constructed; 2, constructing an initial multi-scale graph structure; 3, outputting an inclusion risk probability graph of the current printing layer based on a multi-scale graph growth generation network; 4, inputting the inclusion risk probability graph into a mimicry hummingbird optimization algorithm to generate a path optimization target space; 5, performing path search by adopting a mimicry hummingbird optimization algorithm, and outputting a final scanning path; 6, controlling a laser to perform printing and scanning operation according to the final scanning path; 7, inputting process feedback data into the multi-scale graph growth generation network, and outputting an updated inclusion risk probability graph of a next printing layer; and 8, the step 4 to the step 7 are executed repeatedly till all the printing layers are printed. According to the method, the multi-scale graph growth generation network and the mimicry hummingbird optimization algorithm are fused, and the metal particle inclusion degree is effectively reduced.

The invention provides a PPO-based spacecraft attitude and orbit integrated game control method and device, and the method comprises the steps: building a spacecraft attitude and orbit integrated model, and carrying out the modeling of the interaction process of a tracking spacecraft and a target spacecraft as a non-cooperative zero-sum game; setting a multi-agent deep reinforcement learning framework, wherein the tracking spacecraft and the target spacecraft are respectively configured with an independent strategy network and an independent value network; training is carried out in a double-agent PPO mode, control instructions of orbit thrust and attitude torque are generated through the strategy network, and the state value is evaluated through the value network; and controlling and guiding the behavior of the spacecraft according to the trained strategy. According to the method, the autonomous decision-making capability and cooperative control performance of the spacecraft in complex tasks are effectively improved, and the method is suitable for high-precision aerospace tasks such as interception of non-cooperative targets, autonomous trajectory planning and attitude control.

The invention belongs to the field of aerospace engineering application, and particularly discloses a satellite resource adaptive allocation method and system based on deep intensity learning. The method comprises the steps that a task planning problem model is constructed, ground targets are decomposed into a plurality of optional observation activities based on the model, each ground target corresponds to an independent sub-task in a visible time window of the ground target, and the sub-tasks are defined as meta-tasks; based on the meta-task set, constructing a Markov decision process model; on the basis of a Markov decision process model, a strategy network model based on Transform is adopted, an Actor-Critic algorithm is combined to iteratively optimize a satellite resource allocation strategy for network model parameters, and then a heuristic algorithm is adopted to determine the specific execution sequence and execution time period of each satellite resource provider task. According to the invention, under the condition of limited satellite resources, efficient cooperation of multiple satellites can be realized so as to complete various observation tasks.

The invention relates to a connecting rod configuration separation mechanism for pressing and releasing a stacked satellite assembly, and belongs to the technical field of spaceflight separation mechanisms, the connecting rod configuration separation mechanism comprises a stacking device and pressing separation devices, the stacking device is installed on the corner of each satellite of the stacked satellite assembly, each pressing separation device comprises a pressing mechanism and a rotating mechanism, and the rotating mechanism is installed on the stacking device. The pressing mechanisms are installed on the stacking device of the top satellite, the rotating mechanism is installed on the stacking device of the bottom satellite, the satellites are sequentially stacked through the stacking devices on the corners to form a stacked satellite combination, each pressing mechanism comprises two pressing rods, the pressing mechanisms are connected with the rotating mechanism through the two pressing rods, and the rotating mechanism is connected with the rotating mechanism through the two pressing rods. According to the mechanism, reliable compression connection of a plurality of stacked satellites can be achieved, the action of the mechanism is released from constraint during separation, separation of the stacked satellites is achieved, and the mechanism has the advantages of being simple in structure, large in bearing capacity, small in separation impact, large in separation margin and the like.

The invention discloses a microwave laser hybrid link radio star calibration device and method suitable for deep space exploration, and relates to the field of spaceflight deep space exploration. Pointing calibration of a microwave and laser hybrid link of a deep-space large-aperture antenna is completed through radio star calibration, firstly, after pointing calibration and stable tracking of the microwave link are conducted on the microwave link, fine tracking is conducted on the laser link, pointing calibration of the laser link is completed, respective pointing error correction coefficients are formed, and real-time correction of antenna pointing is achieved. Microwave laser link hybrid radio star calibration is not limited by distance and geographical conditions, and real-time calibration can be realized; the beam of the laser link is narrower than that of the microwave link, the calibration precision is higher, and the system pointing precision and the photoelectric axis consistency precision can be improved. The method is simple in design, high in generalization, low in implementation difficulty and convenient to implement and popularize.

A cabin virtual docking method based on actually measured point cloud data belongs to the technical field of spaceflight docking, and comprises the following steps: acquiring original point cloud data of a cabin structural member; inputting the initial point set into a feature extraction network; the key features comprise decoding features and coding features, the coding features are obtained through the feature processing block, and the decoding features are obtained through the feature recovery block; inputting the extracted key features into a feature segmentation network, segmenting the key features by the feature segmentation network according to categories, and performing parameter fitting on the segmented key features; optimizing matching indexes of the key characteristics after parameter fitting to obtain pose adjustment amounts of the upper cabin section and the lower cabin section so as to realize alignment of butt joint end surfaces and axis superposition of positioning pin holes; and virtual docking between the cabin sections is carried out by using the pose adjustment amount. According to the method, the cabin surface data are directly obtained through measurement, error accumulation is avoided, accurate calculation of the initial relative poses of the two cabins is achieved, and an efficient and reliable solution is provided for high-precision butt joint.

The invention relates to the technical field of spaceflight material forming, in particular to a tension control winding process of a spaceflight carbon fiber composite launch canister, which comprises pretreatment, winding forming, curing and post-treatment. The method comprises the following steps: S1, coating a release agent and a modified coating after processing a core mold, carrying out plasma treatment and eliminating stress; the carbon fiber filaments are soaked in resin containing nanometer components, and are pre-stretched after a hot melting reaction; s2, closed-loop tension control is conducted, winding is conducted according to segmented angles, and modified resin is coated between layers to be overlapped in a crossed mode; s3, stepwise heating and curing, dynamically regulating the pressure and introducing inert gas; and S4, polishing after hydraulic demolding, carrying out sand blasting, carrying out transition layer and ceramic coating, and carrying out multi-dimensional detection. According to the process, the mechanical property and environmental adaptability of the launch canister are improved, the process precision is high, defects are reduced, the forming time is shortened, the rework rate and cost are reduced, the spaceflight requirement is met, and the process is suitable for batch production.

The invention discloses a ground station intelligent equipment management and control system and method for spaceflight measurement and control, and the system comprises a data collection and display module, an intelligent scheduling module, a task execution module, a receiving and forwarding module and the like. Providing a measurement and control plan conflict resolution scheme; satellite macro parameters are configured and automatically issued; receiving, storing, cleaning and forwarding telemetering and remote control data in real time, and generating and pushing a measurement and control task operation report; all the modules cooperate with each other to automatically execute a measurement and control task. Through conflict detection and automatic resolution of the intelligent scheduling module, macro parameter automatic configuration / issuing / unloading of the task execution module and data autonomous processing of the receiving and forwarding module, full-automatic execution of the measurement and control task is realized, the task execution efficiency is improved, manual operation errors are avoided, and the spaceflight measurement and control task efficiency is remarkably improved.

The invention discloses a spaceflight electromagnetic relay failure early warning and diagnosis method based on multi-physics field coupling, relates to the technical field of spacecraft electrical system reliability monitoring, and is used for solving the problems of lack of comprehensive consideration of multi-physics field coupling characteristics under spaceflight special working conditions and low interference resistance to complex environments. The method comprises the following steps: monitoring a network state, obtaining real-time data, calculating an optimal transmission strategy by using an intelligent regulation and control model, dynamically adjusting a coding mode, adaptively adjusting a transmission rate, further ensuring data integrity through an error code detection and error correction mechanism, and adjusting transmission parameters according to a real-time network condition in combination with packet optimization and flow priority management. Effective recognition and early warning of typical failure modes such as contact adhesion and coil burnout are achieved, and the failure early warning accuracy and diagnosis efficiency of the spaceflight electromagnetic relay in complex environments such as high radiation, extreme temperature and strong vibration are improved.

The invention discloses an architecture system and method for large-scale task allocation, and belongs to the field of spaceflight measurement and control, and the system comprises a large-scale hardware device which is used for deploying processing units with different performances and various heterogeneous physical communication link resources; the hardware resource dynamic modeling and visualization framework is used for realizing a dynamic modeling system based on multi-source heterogeneous hardware topology perception; the resource topology awareness database captures and synchronizes system deployment changes by maintaining the dynamic topological relation of hardware resources, presents the life cycle state of the hardware resources, and supports system-level resource situation visualization and decision making; a versioning management engine of component arrangement is applied, a multi-version executable unit is packaged based on an atomization component, and an application instance is completed through a combined modeling component; and deploying a scheduling decision system for deploying a scheduling decision. The method can adapt to task deployment requirements of a current large-scale spaceflight measurement and control system.

The invention discloses a fixing device for a rocket, and relates to the technical field of spaceflight launching equipment, and the device comprises a bearing mechanism which is provided with an embracing clamp assembly and an embracing clamp adjusting assembly for driving the embracing clamp assembly to act; the holding clamp assembly comprises two holding clamp main bodies, each holding clamp main body is provided with a connecting section and a clamping section, the holding clamp adjusting assembly comprises a first mounting seat, a second mounting seat and a limiting seat which are mounted on the bearing mechanism, a driving part is arranged on the first mounting seat, a driving screw rod is rotationally connected between the second mounting seat and the limiting seat, and a driving shaft of the driving part is connected with the driving screw rod; the driving lead screw is provided with a first lead screw section and a second lead screw section which are oppositely arranged in a threaded mode, the driving lead screw is driven by the driving piece to rotate, so that the first driving nut and the second driving nut move along the driving lead screw, then the two holding clamp bodies are driven to rotate relative to the bearing mechanism, and the two clamping sections are matched to clamp or loosen a rocket to be fixed. And the operation process is simple and efficient.

The invention discloses a simulation lunar dust excitation speed measurement system and method under a vacuum plume action condition, and relates to the technical field of aerospace engineering, and the system comprises a vacuum chamber and thruster system, an image collection assembly, a synchronous control collection system, a pulse laser light path, a high-speed spotlight, and a simulation lunar surface. In the invention, two optical systems of particle image velocity measurement and particle tracking velocity measurement are integrated in the same experiment, and the 532nm optical filter and the light trapping sheet are configured to realize compatibility of optical requirements, so that the problems that lunar dust particles with different scales and velocities cannot be measured synchronously and the optical systems interfere with each other in the prior art are solved; according to the method, velocity field data of micron-sized high-speed small particles and millimeter-sized low-speed large particles can be synchronously obtained and directly correspond to each other, the measurement integrity and reliability are improved in combination with simulation environment and synchronous control, and accurate data support is provided for spacecraft lunar dust prevention design.

Combined aerospace system is a multi-stage technology to deliver payloads to orbit and to midair. The system comprises a carrier aircraft, a tow aircraft, a towed spaceplane or a rocket plane or a glider. The carrier aircraft, coupled with the spaceplane and / or the rocket plane or several gliders, takeoff from a runway and ascends to a staging altitude and speed under the carrier aircraft power. After staging, the tow aircraft will pick up the spaceplane or the rocket plane or the glider from the carrier aircraft in flight. The towed spaceplane or the rocket plane or the glider continues ascending and accelerating by the tow aircraft. The spaceplane or the rocket plane will disconnect from the tow aircraft and continue to ascend and accelerate in an atmosphere by using the ramjet engine. The spaceplane or the rocket plane equipped with a propulsion unit is used to place the spacecraft into the earth orbit. The glider will disconnect from the tow aircraft and lands in designated place. Gliders can be used for instantly delivering of correspondence, parcels, and civil goods from a supplier to wide variety of individual consumers or corporate customers.

The invention discloses a microwave laser composite antenna off-axis tracking method suitable for deep space exploration, and relates to the field of spaceflight deep space exploration. According to the method, Ka frequency band link angle tracking is completed firstly, and then a laser link is guided to be captured and tracked rapidly. Microwave link wave beam off-axis tracking is adopted, and simultaneous real-time target tracking of a microwave link and a laser link is achieved; the Ka beam is used for guiding the laser beam to rapidly capture and track, so that the laser beam coarse tracking robustness is improved, and the capture time is reduced; after the laser link finishes fine tracking, the system performs target tracking by using laser beam tracking, and compared with microwave Ka beam tracking, the tracking precision is higher; by using microwave link wave beam off-axis tracking, the problem that microwave link wave beams and laser link wave beams cannot be simultaneously aligned with a target due to inconsistent directions of a microwave electric axis and a laser optical axis is avoided. The scheme is simple and easy to realize, and can be directly applied to the existing integrated antenna.

The invention relates to the technical field of aerospace thermal control, in particular to a thermal control fluid loop, a thermal control system and a temperature control method suitable for a modular satellite. The thermal control fluid loop comprises a pump, a plurality of first pipelines and a plurality of second pipelines; the plurality of first pipelines and the plurality of second pipelines are communicated with each other to form a planar circulating pipeline, and the first pipelines and the second pipelines are respectively arranged along a first direction and a second direction which are orthogonal to each other; the central axes of the first pipelines and the second pipelines are coplanar; the circulating pipeline is filled with a thermal control working medium; the pump is flat, is arranged on the circulating pipeline and is used for providing driving force for flowing of the thermal control working medium; and the thickness of the pump does not exceed 1.5 times of the height of the circulating pipeline. The thermal control fluid loop is high in adjusting capacity, temperature control in a plane can be achieved, and the thermal control fluid loop can adapt to controlled heat source layout of any envelope size; and meanwhile, the thermal control fluid loop adopts a plane structure, so that the requirement of the modular satellite which is folded and unfolded for multiple times on the envelope size in the height direction can be met.

The invention relates to the technical field of aerospace manufacturing and intelligent welding control, and solves the technical problems of insufficient single-mode perception, limited quality prediction precision, lagging parameter regulation and control and weak model adaptive capacity in traditional welding process monitoring. In particular to a spaceflight structure friction stir welding multi-modal sensing and intelligent quality control method, which combines multi-modal real-time sensing and reinforcement learning by introducing a body intelligent body thought, so that a system can autonomously understand a welding state, predict a quality trend and actively adjust process parameters in a welding process; and adaptive optimization control with quality as constraint is realized. According to the method, the limitation of traditional off-line modeling and manual adjustment is broken through, an intelligent control framework with self-learning and self-evolution capacity is provided for spaceflight-level friction stir welding, and a new technical approach is provided for achieving high-consistency and high-reliability welding seams. The intelligent level of friction stir welding of the spaceflight structural part and the welding seam consistency level are remarkably improved.

The invention relates to the technical field of spaceflight sealing, in particular to a multi-mode pressure sealing device and method for heating and extracting extraterrestrial star soil gas. The device comprises a transposition sealing disc, a positioning base disc and a distributed driving actuator, a flow guide funnel is arranged on the outer side of the transposition sealing disc, and a sample receiving station and a sealing station are arranged on the inner side of the transposition sealing disc; an interface cylinder is arranged on the outer side of the positioning base disc, and a sample receiving station hole is formed in the inner side of the positioning base disc; the distributed driving actuator is connected with the transposition sealing disc and the positioning base disc and used for driving the transposition sealing disc to conduct axial rising, station switching and axial sealing relative to the positioning base disc in a time-sharing mode. The problem of dynamic sealing failure under the extreme temperature difference and high particle invasion environment can be effectively solved, zero-leakage collection of star soil heating gas is achieved, the reliability and operation efficiency of gas sample collection in a deep space exploration task are remarkably improved, and mechanical interference or positioning deviation caused by compound motion of a traditional linkage mechanism is also avoided.

The invention relates to a three-dimensional microgravity simulation system, and belongs to the field of spaceflight mechanism ground tests. According to the three-dimensional microgravity simulation system, ground six-degree-of-freedom microgravity simulation can be realized, the aircraft simulator and accessories thereof have a five-degree-of-freedom motion state on an air floating plane through the five-degree-of-freedom air floating platform, and the aircraft simulator can have a three-dimensional space six-degree-of-freedom motion state through the magnetic air suspension assembly. In the process of a ground microgravity experiment, the gravity of the movement of the aircraft and accessories thereof is unloaded by the magnetic suspension assembly, so that the movement interference of the aircraft simulator and the microgravity simulation tool is avoided, and the problem of dynamic high-precision gravity unloading is solved.

The invention relates to an anti-radiation D flip-flop based on interconnection line crosstalk calculation. The anti-radiation D flip-flop comprises a cascade structure of a master latch module and a slave latch module, the primary latch module converts an input signal into a dual-node redundant signal through a first interconnection line crosstalk circuit (CC1), and logic storage of triggering high output only by dual high input is realized by capacitive coupling of L1-L3 and L2-L3; the slave latch module generates redundant signals L4 / L5 through a second interconnection line crosstalk circuit, and error correction is carried out on CC2 output and direct transmission signals in combination with a Muller C unit. The D flip-flop only needs 16 transistors with the minimum size, and the number of the transistors is reduced by 67% compared with that of a traditional TMR; asynchronous reset is supported, and the L3 / L6 is forced to be charged to a high level during reset; the capacitive coupling strength is controlled through metal layer wiring, and the reliability of a spaceflight electronic system in a radiation environment is remarkably improved.

The invention discloses a multi-engine vacuum plume field rapid calculation method based on deep learning, and relates to the technical field of aerospace propulsion systems and computational fluid mechanics, and the method comprises the following steps: sample data acquisition, data preprocessing, feature extraction, mapping relation construction, and flow field rapid calculation. According to the method, multi-dimensional feature representation is achieved through a symbol distance function, an identifier matrix and a free initial field, a deep learning agent model is constructed by combining data driving and physical constraint loss function design, the multi-engine plume complex interference effect is effectively processed, the prediction error of a key area is reduced, and the extreme working condition generalization ability is enhanced; meanwhile, traditional high-cost simulation is replaced, the flow field calculation efficiency is improved, and an efficient and accurate scheme is provided for spacecraft plume analysis and engineering application.

The invention discloses a multi-satellite cooperative operation method based on measurement and control link optimization, and relates to the technical field of spaceflight measurement and control and satellite communication optimization, and the method comprises the steps: obtaining the orbital elements of all satellites in a target constellation and the geographic coordinates of ground measurement and control stations, calculating the visible time windows of all satellites and all measurement and control stations, and generating a visible window matrix; constructing a link quality evaluation model to obtain a link quality index; distributing measurement and control time slots by using a weighted optimization algorithm, and generating a time slot distribution matrix; issuing a measurement and control instruction to each satellite and each measurement and control station, acquiring a link quality measured value, and comparing the link quality measured value with a link quality index to obtain a comprehensive link quality deviation value; and when the comprehensive link quality deviation value exceeds a preset threshold value, marking unexecuted measurement and control time slots in the time slot distribution matrix, and redistributing the unexecuted measurement and control time slots to generate an updated time slot distribution matrix, thereby realizing self-adaptive cooperative operation of the multi-satellite measurement and control link. According to the invention, dynamic optimal configuration of multi-satellite measurement and control resources is realized.

The invention relates to the technical field of spaceflight microwave remote sensing, and provides a spaceborne synthetic aperture radar in-orbit autonomous task planning method, device and equipment, and the method comprises the steps: obtaining imaging parameter information; the imaging parameter information is determined by the satellite imaging system based on task annotation information, orbit information and an imaging parameter preset table, and the task annotation information is obtained by the satellite imaging system by analyzing observation requirements of a user; the orbit information is determined based on satellite forecast information. According to the method, imaging parameter information is determined by a satellite imaging system based on task uploading information, orbit information and an imaging parameter preset table, partial parameter calculation and instruction generation processes of traditional satellite-borne SAR task planning are moved to a satellite, manual calculation and ground uploading steps are omitted, and dependence of the task planning process on ground calculation is reduced; the task uploading information is obtained by analyzing the observation demand of the user through the satellite imaging system, the observation demand can be uploaded in advance, satellite resources are fully utilized, and the task execution efficiency is greatly improved.

The invention provides a satellite power supply system topology architecture and a maximum power point tracking control method thereof, and aims to improve the energy utilization efficiency of a solar cell array of a spinning body spacecraft under a complex illumination condition. The architecture adopts a combined topology architecture of a preceding-stage sequence switch maximum power point shunt regulation (S3MPR) circuit and a backward-stage four-switch Buck-Boost (FSBB) converter, and is suitable for a special operation environment of a spinning body spacecraft power supply system. The system adopts a bus full adjustment mode, enables the DC bus voltage to be stabilized near the maximum power point voltage of the photovoltaic array through a double closed-loop control strategy, and carries out real-time shunting adjustment on an S3MPR circuit in combination with a multi-peak maximum power point tracking (MPPT) algorithm, thereby ensuring the efficient operation of the photovoltaic array. According to the invention, high-efficiency energy tracking and stable charging can be realized under a complex illumination condition, and the reliability and the energy utilization rate of a spinning body spaceflight power supply system are remarkably improved.

The invention relates to a satellite-borne electronic hardware design guarantee method and system. The method comprises the following steps: determining a satellite-borne hardware guarantee level (SHL) of satellite-borne electronic hardware; integrating a fault mode injection FM I into a design process of satellite-borne electronic hardware, and adjusting the execution depth of the FM I based on the SHL level; and providing a process cutting engine, and realizing adaptive process cutting based on a DO-254 standard according to the SHL level and in combination with the execution depth of the FM I. The system comprises an SHL evaluation module; an FM I management module; a space environment effect knowledge base; and a process cutting engine. According to the method, the problem that the DO-254 standard is insufficient in adaptability in the aerospace field is solved, the reliability design and verification efficiency of satellite-borne electronic hardware is remarkably improved, and the method is suitable for aerospace tasks such as various satellites and deep space probes.

The invention discloses a cloud measurement and control comprehensive operation platform system and method based on micro-service, and belongs to the technical field of aerospace measurement and control and micro-service software combined application, and the system comprises an infrastructure layer module which is used for carrying out virtualization on aerospace equipment and providing basic calculation, storage and network resources for service operation; the cloud platform layer module is used for realizing unified management and scheduling of heterogeneous diversified resources; the service support layer module is used for performing unified management on various business services and providing universal middleware for functional services; the heterogeneous computing power arrangement layer module is used for realizing management, arrangement and scheduling of various resources and carrying out resource recombination and allocation in a resource pool according to a task instruction of a service function layer; the business function layer module is used for realizing business functions of the system; and the terminal layer man-machine interaction module is used for displaying system tasks, equipment and information. According to the method, the rapid development requirements of a baseband hardware platform towards generalization, standardization and cloudization can be met.