202 results about "Deep space exploration" patented technology

The invention discloses a lunar balance dynamic parameter high-precision resolving method and system combining LRR and LLR technologies, and belongs to the field of deep space exploration and celestial body dynamics, and the method comprises the steps: constructing an LRR and LLR combined observation data set, and carrying out the preprocessing; constructing an LRR and LLR combined moon measurement model, and deducing a partial derivative of the model for a moon rotation parameter and a tidal LOVE number to obtain a combined partial derivative matrix; iterative solution is carried out through nonlinear least square to obtain dynamic parameters of the moon balance; and evaluating a resolving result and optimizing a resolving strategy, and optimizing a resolving scheme by dynamically adjusting the weight, improving a tide model and eliminating abnormal values. According to the method, the parameter calculation error is reduced, the technical advantages of two types of data are effectively integrated, the problem of insufficient observation continuity or precision of a single data source is solved, and reliable parameter support is provided for moon rotation and internal structure research.

The invention discloses a planetary atmospheric trace gas spectrum telemetering and in-situ fusion detection system and method, and belongs to the technical field of deep space exploration. The detection system has a telemetering mode and an in-situ detection mode, and comprises a telescope module, a laser light source module, a heterodyne spectrum telemetering module, an in-situ absorption spectrum module, a gas sampling and enriching module and a signal acquisition, processing and control module. In the on-orbit stage, a heterodyne spectrum telemetering module is adopted, and a laser light source and sunlight signals are subjected to frequency mixing for atmospheric component telemetering; and after the detector enters an atmospheric descending section, the in-situ absorption spectrum module performs in-situ absorption spectrum measurement by utilizing the detection light of the same laser light source. By performing space-time fusion and joint inversion on the data acquired in the two modes, coherent detection from large-range general survey to fixed-point detailed survey is realized, the problems of load separation of telemetering and in-situ detection and difficulty in data fusion are solved, and the detection efficiency, the data consistency and the integration level of the system are greatly improved.

The invention discloses a high-precision quantum sensing environment physical quantity real-time monitoring system and method, and belongs to the technical field of environment monitoring. The system comprises a quantum sensing front end, a signal excitation and regulation module, a quantum classical hybrid computing engine, an edge cloud collaborative transmission module and a terminal application module. The quantum sensing front end adopts a quantum entanglement sensing array integrated by NV color center diamond and a rubidium atom gas chamber to synchronously sense a magnetic field, temperature, pressure and vibration; the signal excitation and regulation module optimizes regulation parameters and inhibits noise through a quantum optimal control algorithm; a quantum-classical hybrid calculation engine is combined with a quantum neural network and classical multi-algorithm collaboration to realize efficient resolving and data fusion of quantum state features. According to the invention, the monitoring precision, the real-time response speed and the anti-interference capability are obviously improved, synchronous monitoring of multiple physical quantities is supported, and the system is suitable for various scenes such as industry, scientific research and deep space exploration, and has wide application value.

The invention discloses a deep space exploration low-power-consumption AI navigation algorithm processing system based on a storage and calculation integrated architecture, the system adopts the storage and calculation integrated architecture based on RRAM cross arrays and calculates an AI navigation algorithm, the system comprises an RRAM storage and calculation core, a dynamic configuration PE array, an anti-radiation controller and an on-chip storage interaction unit, the RRAM storage and calculation core comprises a plurality of independent RRAM cross arrays, in-situ execution of matrix-vector multiplication and vector-matrix multiplication is supported; the dynamic configuration PE array is used for processing nonlinear operation, and dynamic switching of two parallel granularity modes of 16 * 16 and 4 * 4 is supported through a configuration register; the anti-radiation controller is used for repairing radiation induction errors in real time and coordinating task scheduling of the storage and calculation core and the PE array; and the on-chip storage interaction unit adopts an SRAM (Static Random Access Memory) as an intermediate cache and is used for temporarily storing intermediate data. The problem of high power consumption of an AI navigation system for extreme environment detection can be solved.

The invention relates to the technical field of deep space detection equipment, in particular to an extraterrestrial celestial body rock coring drill and a coring and breaking method thereof. The coring drill comprises an attachment mechanism, a rotary impact sliding table mechanism and a coring and core breaking mechanism which are sequentially connected, the attachment mechanism is used for being anchored to the surface of celestial rock, and the rotary impact sliding table mechanism is used for providing drilling rotation, impact power and axial feeding motion; the coring and breaking mechanism comprises an outer drill bushing, an eccentric coring pipe assembly mounted in the outer drill bushing and a drill bit connected to the front end of the outer drill bushing; the eccentric coring pipe assembly comprises a coring pipe and a driving shaft for driving the coring pipe to rotate, and the coring pipe and the driving shaft are eccentrically arranged; the driving shaft can be controlled to synchronously rotate in the same direction with the outer drill bushing or independently rotate in the opposite direction relative to the static outer drill bushing. Active anchoring and multiple buffering are combined, the sample integrity, the operation success rate and the automation degree of extraterrestrial hard rock coring are remarkably improved, and lossless capture and mechanical reliable breaking of a rock core are achieved.

The invention discloses a simulation system and a simulation method for a deep space tracking measurement task, and relates to the technical field of deep space exploration tracking measurement. The system comprises a task simulation and visualization subsystem which is used for carrying out environment parameter configuration and task state control on a deep and far space simulation task and outputting operation information; the data set construction and verification subsystem is used for generating a navigation verification data set and performing functional performance simulation verification; and the algorithm performance evaluation subsystem is used for constructing a performance evaluation index system and evaluating the tracking measurement algorithm. According to the invention, integration of tracking measurement technologies such as space reference, one-way measurement, autonomous orbit determination, landing and patrol navigation and the like of deep and far space tasks and planet calendar, detection tasks and aircraft state simulation can be realized, test verification based on in-orbit actual measurement data is carried out, and a unified and standard evaluation index system is provided; the problem that an existing deep space task simulation system cannot provide accurate reference for a deep space ultra-large spatial-temporal scale simulation system is solved.

The invention discloses a nonlinear system dynamic boundary constraint particle filtering method, and belongs to the technical field of deep space exploration. The implementation method comprises the following steps: independently sampling all nodes of the flexible lander, and introducing constraints in a particle filtering initial sampling link to enable initial particles to meet the constraints; in the filtering process, as many particles as possible fall within the constraint range in the initial stage of filtering by widening the constraint boundary, and the constraint boundary is continuously shrunk to be gradually close to the real constraint range, so that the situation that a large number of particles fall out of the constraint boundary due to the fact that the real constraint range is too narrow is avoided. According to the method, the constraint boundary is dynamically adjusted, the number of effective particles is increased, and a higher-precision multi-node state estimation result of the flexible lander is obtained; according to the multi-node state of the flexible lander, the particle diversity is ensured through dynamic scaling constraint boundaries, and filtering stop caused by particle degradation is prevented; and realizing real-time trajectory planning and guidance control of the flexible lander by using a node state estimation result.

The application provides a variable configuration spacecraft system and method for non-cooperative target capture, and belongs to the field of deep space exploration. The method comprises the following steps: 1) a rigid combination flies to the vicinity of the target; 2) the combination is spun to be expanded into a ring belt; 3) the ring belt envelopes the target; and 4) the ring belt encloses the target. Large space debris and small celestial bodies both belong to non-cooperative targets, and cannot provide special interfaces for assisting capture. It is extremely difficult to develop general control mechanisms and methods to realize reliable capture and stable connection of various targets. In order to solve the problem, the application utilizes the inter-satellite connection to expand a plurality of controllable satellites into a ring-shaped multi-body tether satellite formation system, and carries out ring belt enveloping and then enclosing the tether to realize capture of a non-cooperative target with large scale, complex geometric shape, great uncertainty of motion state and inertia information according to a predetermined trajectory. The application has the advantages of high applicability, flexibility, high intelligence, reusability and small size.

This invention relates to a multi-constraint trajectory planning method for bouncing movement on the surface of complex small celestial bodies, belonging to the field of deep space exploration. The implementation method is as follows: Establishing a closed-form relationship between bouncing movement distance, velocity, takeoff angle, and energy consumption, and a two-layer expansion radius obstacle representation model; establishing escape velocity constraints, no-fall constraints, fly-through feasibility constraints, and convex obstacle fly-through constraints; using the two-layer expansion radius obstacle representation model and multiple constraints, establishing a fly-through feasibility determination mechanism for obstacles; using Poisson-disk sampling to establish the bouncing reachability domain and an analytical solution for the energy-optimal trajectory satisfying multiple constraints; establishing a reachability domain filtering method based on the bouncing reachability domain and the analytical solution for the energy-optimal trajectory; using energy consumption as the weight, employing the A* algorithm to search for a global energy-optimal bouncing path point sequence and the corresponding velocity and takeoff angle of each path point, generating a global energy-optimal trajectory, thus realizing multi-constraint trajectory planning for bouncing movement on the surface of complex small celestial bodies.

This invention provides a method and system for high-fidelity physical modeling and detection performance evaluation of space targets, relating to the field of deep space exploration technology. The method first acquires the relative motion parameters of the spacecraft and the asteroid, as well as camera parameters, and determines the static apparent magnitude based on observation geometry and the asteroid's physical characteristics. Then, it calculates the angular velocity modulus through relative velocity, combines it with camera parameters to obtain tail parameters, and quantifies the equivalent magnitude loss and effective apparent magnitude based on a piecewise model. Subsequently, it constructs a two-dimensional parameter grid of focal length and exposure time, calculates the effective signal-to-noise ratio and detection margin for each combination, and selects the optimal parameters using a heatmap. Finally, it generates a high-fidelity simulation image and feeds back the observation values ​​to the guidance, navigation, and control system via a UDP asynchronous interface. This invention achieves quantitative assessment of tail loss and automated parameter optimization, balancing high fidelity and real-time performance, and improving detection accuracy and system reliability.

The invention discloses a space science data collaborative computing method and system based on a no-service computing architecture. According to the method, the technical problems that in traditional space science data processing, resource elasticity is insufficient, multidisciplinary cross-domain heterogeneous computing environment collaboration is difficult and data islands are serious are solved by constructing a whole-process and service-free computing framework of data access-function encapsulation-collaborative scheduling-result aggregation. Specifically, tasks such as preprocessing, analysis and modeling of space science data are packaged into a lightweight and non-service calculation function, data calculation collaborative calling in the interdisciplinary field is achieved in combination with a multi-calculation-node permission management mechanism, and calculation resources are distributed according to needs through a dynamic resource scheduling algorithm. The multi-disciplinary cross-domain TB / PB-level spatial data processing method has the advantages of being high in resource utilization rate, low in operation and maintenance cost and high in expansibility, and can be widely applied to space science research scenes such as sun-earth space physics, deep space exploration and high-energy celestial body outbreak.

This invention relates to an on-orbit high-density storage and supply device and method for electric propulsion working propellant, belonging to the field of spacecraft deep space exploration and on-orbit servicing technology, which can effectively save space and mass resources of spacecraft. The cooling circuit consists of a storage tank, a refrigerator, a pump, and an injection pipe connected sequentially; the pressurization circuit consists of a storage tank, a heating evaporator, and a third solenoid valve connected in a loop; and the gaseous working propellant circuit consists of a storage tank, a vaporizer, and a buffer chamber connected sequentially. This invention simplifies the complexity of the propulsion system and reduces potential failure risks, effectively supporting the application of high-power, high-specific-impulse, and long-life new electric propulsion technologies, providing important support for deep space exploration and on-orbit servicing missions.

This invention provides a rapid exposure adjustment system and method for high-speed space cameras, belonging to the field of deep space exploration. Combining camera image grayscale statistics and PIN tube metering technology, it integrates the advantages of two traditional exposure time adjustment methods. This system can meet the needs of rapid exposure time adjustment for high-speed cameras in transiently bright scenes, avoiding overexposure of consecutive images due to transient brightness caused by impacts. Simultaneously, it can achieve fine-tuning of exposure time in scenes with gradually changing targets, ensuring imaging effects on sputtering clouds generated by impacts. This invention implements an exposure time adjustment method that combines fast and slow adjustments, as well as coarse and fine adjustments, effectively guaranteeing imaging effects in complex scenes throughout the entire kinetic energy impact process.

The application discloses a double-gas-chamber neutron detector, belonging to the technical field of nuclear radiation detection and particle detection, comprising a gadolinium film neutron conversion layer, two time projection chamber (TPC) modules and an optional energy quantifier module. After capturing thermal neutrons, the gadolinium film generates multi-state particles, and the two TPC modules realize 4π solid angle neutron detection through electronic signal coincidence. The application replaces the scarce 3 He with gadolinium, combines the track reconstruction capability of the double TPC module, significantly improves the neutron detection efficiency and signal-to-noise ratio, and is suitable for nuclear reactor monitoring, industrial material analysis, agricultural moisture detection and deep space exploration and other fields. Through electronic-gamma coincidence measurement and mode recognition, high-precision neutron signal reconstruction and environmental background suppression are realized.

The application provides a Mars crater detection method and system, relates to the technical field of planetary remote sensing image processing and target detection, and comprises the following steps: constructing a CAFE-Net network based on a YOLO single-stage detection model, integrating a multi-scale context perception module, a feature enhancement unit and an efficient feature fusion network, training the model after pre-processing MDCD and DACD data sets, and outputting visualized and structured detection results through model inference and non-maximum suppression post-processing, so that the problems of high false detection rate of craters and dome structures and high missing detection rate of small craters in the prior art are effectively solved, the precision and recall rate are improved, the method is suitable for deep space exploration scenes such as Mars probe landing site selection and Mars geological age determination, and can be automatically processed in an end-to-end mode and is convenient to deploy.

The invention relates to a high-speed unmanned Mars rover capable of actively switching suspension modes, and belongs to the technical field of deep space exploration, the high-speed unmanned Mars rover comprises a walking frame, a suspension and a switching mechanism, the walking frame comprises a rover frame, a connecting beam, two swing arms and two connecting rods, the suspension comprises an outer fixing plate and a lower shock absorber, and the switching mechanism comprises a rotating shaft, an outer moving plate and an actuator. The two ends of the lower shock absorber are connected to the lower frame and the outer fixing plate correspondingly firstly, then the rotating shaft fixed to the upper frame slides in the curve hole, the linear hole and the expanding hole in a switching mode, when the unmanned Mars rover is parked, the rotating shaft slides in the curve hole to level the rover frame, and when the unmanned Mars rover runs at a low speed, the rotating shaft slides in the curve hole to level the rover frame. The rotating shaft slides in the linear hole, so that the frame swings along with the two swing arms, when the unmanned Mars rover runs at a high speed, the rotating shaft slides in the diameter expanding hole, vibration and shock absorption on the two swing arms are transmitted to the frame, and switching of the suspension among a flexible suspension, a passive suspension and a rigid suspension is achieved.

The invention discloses a Mars in-situ carbon dioxide cooling supply nuclear energy power generation system, belongs to the technical field of nuclear energy power generation systems, and particularly relates to an extraterrestrial celestial body in-situ resource utilization (ISRU) nuclear energy power generation technology. The problems that an existing Mars closed Brayton cycle nuclear power generation subsystem is difficult in heat dissipation and difficult in working medium supply are solved. The system comprises a carbon dioxide liquefaction subsystem and a closed Brayton cycle nuclear power generation subsystem. The Mars in-situ carbon dioxide cooling replenishment nuclear energy power generation system is suitable for deep space exploration and extraterrestrial energy utilization.

This invention belongs to the field of space laser communication and deep space exploration technology, and discloses an integrated detection device for space laser communication monitoring and interaction. The device includes a main body, on which are integrated a solar panel, a navigation imaging device, a communication antenna, a communication receiver, a radar, a landing support, and functional components for communication monitoring, environmental perception, and interactive operation. This invention forms a closed-loop system through electrical, signal, and mechanical connections, enabling simultaneous execution of multiple tasks, significantly improving the device's space operation efficiency, reducing the load pressure on space launch vehicles, and adapting to the space constraints of on-orbit operations. The communication antenna and receiver achieve bidirectional signal interaction through a high-speed laser communication module and are linked with the navigation imaging device and environmental sensors to ensure stable transmission and status monitoring of laser communication signals, which is beneficial for practical applications and operations.

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.

The invention belongs to the technical field of deep space exploration, and particularly relates to a multispectral image displacement depth adaptive mapping method and system based on radiometric calibration, and the method comprises the steps: obtaining original black field data with the input bit depth being N and original flat field data with the input bit depth being N; after bad pixels are shielded according to the original black field data and the original flat field data, row offset and row response are calculated; sequentially determining a global scale according to the row offset and the row response, calculating an integration slope, and generating a lookup table according to the integration slope; and acquiring real-time monitoring input, reading the M-bit output value corresponding to the real-time monitoring input according to the lookup table, and correcting and updating the lookup table according to the M-bit output value. Based on a parameterized calculation process (derivation from row bias and row response to a global scale and an integrated slope), different input bit depth and output bit depth requirements can be met by modifying input parameters, inherent limitation caused by hard coding is avoided, and the configurability of cross-platform tasks is improved.

This invention relates to an inter-satellite laser multi-standard signal fusion time-frequency synchronization method and system. It integrates frequency synchronization, time synchronization, and communication functions by using a single laser source to carry a frequency signal, a single-frequency signal, a low-pass filtered signal, and a pseudo-random code signal with communication data via spectrum shifting. The three signal spectra are separated and do not interfere with each other. The frequency signal is used for inter-satellite frequency synchronization; the single-frequency signal is used for high-precision time delay measurement to achieve inter-satellite time synchronization; and the pseudo-random code signal serves both communication and time delay measurement ambiguity resolution. This invention employs a bidirectional time delay measurement and joint calculation method, combined with frequency signal link jitter compensation, to achieve parallel and collaborative operation of the three functions. Compared with existing technologies, this invention improves system integration, reduces the number of modules and external interfaces, and effectively reduces the weight, power consumption, and volume of onboard equipment. It is suitable for high-precision time-frequency synchronization applications such as satellite navigation, deep space exploration, and integrated space-ground networks.

The application discloses a bionic variable stiffness interlocking structure suitable for a planetary lander and a preparation method, and relates to the technical field of deep space exploration. The bionic variable stiffness interlocking structure of the application reserves a gap, an auxiliary rib or a cylinder as a weak end, the weak part is preferentially dissipated damage under load, and the overall secondary stiffness change is realized through truss fitting and locking and compression. The application adopts a partition functional arrangement, uses a martensite dominant nickel-titanium alloy lattice support in a landing impact energy absorption part, relies on martensite reorientation to realize efficient energy dissipation, low residual strain and shape recovery, uses an austenite dominant nickel-titanium alloy lattice support in a main load bearing core area, and uses the high modulus and buckling resistance characteristics to guarantee the structure stiffness and stability. Through the collaborative combination of the two types of alloy units, the load bearing, buffering and adaptive variable stiffness integration are realized, the planetary landing process multi-load coupling working condition requirements can be effectively met, and the structural reliability and buffering performance of the lander under deep space extreme environment are improved.

The present application relates to the field of spaceflight TT&C technology, and specifically discloses a method and system for implementing an extraterrestrial object blocking TT&C plan under deep space large time delay conditions. The present application determines extraterrestrial object blocking time windows and ground available tracking stations by using precise orbit data of a probe, calculates station prediction containing data truncation and one-way light time of uplink and downlink signal transmission, sets uplink tracking events in advance and downlink tracking events in arrears according to the one-way light time, merges adjacent TT&C arcs with a time interval less than a preset threshold into single-station continuous tracking arcs to set task preparation events, and decouples uplink and downlink under deep space TT&C mode, controls transmission of uplink carriers and remote control instructions according to the one-way light time, thereby solving the technical problems of difficulty in space-earth cooperation and poor timeliness of emergency retransmission during extraterrestrial object blocking under deep space large time delay conditions, and improving the reliability and timeliness of implementation of deep space exploration mission TT&C plans.

This invention relates to the field of optical thin film fabrication technology, specifically to a method for fabricating a high extinction ratio, adhesive-free polarizing beam splitter film resistant to high and low temperature environments. The method includes the following steps: S1, substrate pretreatment; S2, polarizing beam splitter film deposition; S3, adhesive-free bonding treatment; S4, annealing strengthening; and S5, post-treatment. This invention uses an adhesive-free optical contact bonding process to replace the traditional organic bonding process, completely eliminating the temperature adaptability bottleneck caused by organic adhesive layers. The bonding interface relies on intermolecular forces for adhesion, eliminating problems such as aging and debonding of organic adhesives. This allows the device to operate stably in a wide temperature range of -60℃ to 120℃, greatly improving the device's environmental adaptability and meeting the needs of extreme environments such as deep space exploration and polar observation.

The application discloses an integrated flexible communication system compatible with FDD and TDD, which comprises a radio frequency transmitting unit, a radio frequency receiving unit, a continuous signal processing unit, a special signal processing unit, a burst signal processing unit and a state machine control unit. The application recombines the physical layer, the coding and synchronization sublayer, the MAC sublayer, the frame sublayer, the I / O sublayer and the network layer in the FDD communication system and the TDD communication system according to the function implementation mechanism, breaks the traditional layered architecture, fuses the common modules dispersed in each sublayer according to the large data processing mechanism and the scheduling control processing mechanism, trims the control and signal processing units exclusive to each sublayer, greatly reduces the processing and scheduling overhead in the traditional layered implementation mode, and reduces the hardware implementation complexity of each function mechanism, thereby most supporting the stringent requirement of the deep space exploration task on product miniaturization.

The invention discloses a self-correction state forecasting and fusion estimation method for a Mars pneumatic auxiliary orbit descending model, and belongs to the technical field of deep space exploration. The implementation method comprises the following steps: integrating various perturbation of a detector, and establishing a dynamic model suitable for long-term orbit extrapolation; the orbiter observes a natural large landmark on the surface of the Mars by using a navigation camera to obtain azimuth information of the landmark; when the detector is far away from the Mars, azimuth information of the Mars is obtained through the navigation camera; when the distance is closer to the Mars, observing a satellite surface landmark, and acquiring azimuth information of the landmark; the detector and the orbiter measure the relative distance and orientation through radio, and the measurement information obtained through fusion corrects the extrapolation result of the orbit. When the detector is located in the atmosphere, an accelerometer is used for measuring the external force acceleration of the detector, and inertial navigation is achieved. The atmospheric density is corrected by using the dynamic pressure and the heat flux density, and re-recursion is performed on the state of the detector, so that the state estimation precision of the detector in the Mars atmosphere is improved.

The invention provides a vehicle power system suitable for lunar polar region exploration and a verification method, and relates to the technical field of deep space exploration, the system comprises a configurable energy module, a driving motor transmission mechanism, a power conversion management system, a thermal control subsystem and an autonomous driving controller; the energy module comprises a space fuel cell module, a wide-temperature lithium ion battery module, a solar cell panel module and a radioactive isotope battery module, and one or more of the modules can be selected to be combined according to task requirements. According to the invention, full-scene energy supply coverage of the monthly day, the monthly night and the permanent shadow area can be realized, uninterrupted propulsion of detection and transportation tasks is supported, and the task execution efficiency and the detection coverage range are greatly improved; meanwhile, it can be ensured that the driving power is accurately matched with the driving requirement of the complex terrain in the polar region of the moon, the driving power calculation deviation is effectively reduced, and the terrain passing capacity and operation stability of the vehicle are remarkably improved.

The invention relates to the field of copper foil composite materials, in particular to a composite copper foil for deep space exploration of a battery current collector and a preparation method and application of the composite copper foil. The nano-composite reinforced core layer is a composite copper matrix obtained by pulse electrodeposition; the high-conductivity surface layer is a copper layer which is epitaxially grown on the composite copper substrate by direct current deposition, and the copper layer is provided with a gradient structure for gradually increasing the conductivity of the composite copper substrate from inside to outside; the self-adaptive passivation layer is an amorphous composite ceramic protection layer used for preventing the high-conductivity surface layer from being oxidized. The nano-sized graphene with defects is introduced in the preparation process, and parameters of each step are accurately controlled, so that the comprehensive performance of the copper foil is improved, and the requirement of high-energy density design of the lithium ion battery is met.

The invention discloses a calculation method for determining satellite azimuth pitching through TLE data, relates to the technical field of satellite azimuth pitching calculation, and remarkably improves the cooperation precision of satellite azimuth pitching angle calculation by dynamically calibrating the local UTC time of multiple ground stations. In scenes of satellite measurement and control, deep space exploration, emergency communication and the like, according to a traditional method, due to clock asynchronism, calculation results of all stations are inconsistent, and beam pointing or relay tracking continuity of an antenna array is affected; according to the method, the satellite position deviation is creatively utilized to reversely deduce the time error, the space deviation is mapped into the time calibration amount, the time reference is directly unified from the data level, and high-cost deployment depending on external clock synchronization equipment is avoided.

The invention discloses a lightweight space satellite detection positioning method, a hardware architecture and a space probe, and relates to the technical field of deep space exploration. The method comprises the following steps: receiving and preprocessing a space environment image; constructing a lightweight convolutional neural network model, wherein the lightweight convolutional neural network model comprises a multi-scale convolutional feature extraction and fusion module and a decoupling multi-scale detection head module; processing the received space environment image through a multi-scale convolution feature extraction and fusion module, and generating a feature map fusing multi-scale semantics and space details; and performing parallel classification prediction, foreground prediction and bounding box regression on the fused feature map through a decoupling multi-scale detection head module, and outputting a satellite target detection result. According to the method, semantic information and spatial details of target features are enhanced through multi-scale convolution feature extraction and fusion, the detection effect of a small target is remarkably improved, and the model can be deployed on a satellite-borne FPGA chip with limited resources through deep pruning and quantitative design.