369 results about "Deep space exploration" patented technology

The invention discloses a high-performance satellite platform based on a real-time operating system and a wireless bus and a working method of the high-performance satellite platform, and belongs to satellite communication technologies, future deep space exploration and low-orbit satellite constellations. On the basis of an original structure of a satellite platform, a real-time operating system is effectively combined with a wireless bus system, and the real-time operating system comprises a kernel module, a communication module, an equipment driving module, a file system module, an application interface module, a safety module and a fault management module. The wireless bus system comprises a physical layer, a data link layer, a network layer, a transmission layer and an application layer. According to the invention, efficient and reliable communication and task execution capabilities are provided for a satellite platform, the requirements of real-time performance and reliability of a satellite in a complex environment are effectively met through modular design and tight work of the system, and meanwhile, complex lines and interfaces brought by a wired system are avoided.

The invention discloses a scene understanding and intelligent decision-making method for a planet probe vehicle in a complex unknown environment, and relates to the technical field of deep space exploration and intelligent vehicles, and the method comprises the steps: obtaining multi-dimensional environment information; constructing a slump function based on the geometric morphology, motion characteristics and material attributes of the obstacle, and dynamically quantifying the risk of the obstacle; smoothing the potential field function by adopting Gaussian filtering, and dynamically adjusting the weight of a global potential field and the weight of a local potential field; in combination with an improved clustering algorithm, fuzzy regions of obstacles capable of being crossed and obstacles not capable of being crossed are accurately divided; screening passable areas by constructing a credibility mean square value function; carrying out multi-objective optimization by adopting a genetic algorithm, and generating an optimal path matched with the environment in cooperation with an offline data set and online reasoning; and inputting the optimal path into a bottom layer control system of the probe vehicle, controlling execution of a motor driving and steering mechanism, monitoring the state of the probe vehicle in real time, and triggering dynamic re-planning. And the autonomous obstacle avoidance capability and the path planning efficiency of the probe vehicle in a complex environment are improved.

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.

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 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 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.

A self-sensing self-adaptive deformable wheel tensioned and integrally supported by a paper folding configuration shape memory alloy wire belongs to the technical field of mechanical engineering and robots and is composed of a paper folding deformable module, a self-sensing module and a driving module, and the modules cooperate to realize the functions of wheel diameter dynamic adjustment, load self-sensing, terrain self-adaptive deformation and rigid-flexible coupling adjustment. The paper folding deformable module is designed based on an improved water bomb inlaid paper folding pattern, and an overlapping face, a small flexible piece and an additional face are additionally arranged to improve deformation flexibility. The self-sensing module comprises a tensegrity structure, continuous rigidity switching is achieved through pre-tightening force adjustment, and the load is monitored in real time through the strain-resistance effect of a shape memory alloy wire; and the driving module is directly driven by a radial electric push rod to realize wheel diameter change to adapt to terrains. By means of the structure-sensing-driving integrated design, the intelligent self-adaptive robot has the advantages of being light in weight, high in bearing capacity and intelligent and self-adaptive, and is suitable for complex terrain moving platforms such as deep space probe vehicles and disaster relief robots.

The invention provides a deep space exploration simulation test system and method.The deep space exploration simulation test system comprises a thermal interface structure, a cryogenic subsystem and a heating structure, the cryogenic subsystem can refrigerate and cool the thermal interface structure, and the heating structure can heat the thermal interface structure; the deep cooling subsystem comprises a low-temperature refrigeration assembly and a gas cooling assembly, the low-temperature refrigeration assembly transmits cold energy to the thermal interface structure in a one-way mode, and the gas cooling assembly cools the thermal interface structure through cooling gas. The continuous temperature regulation in the range of 300K to 423K is realized through the combination of air cooling and electric heating, and the continuous temperature regulation in the range of 38K to 300K is realized through the combination of a G-M low-temperature refrigerator and electric heating; compared with the existing space environment simulation equipment, the temperature zone can be expanded to 38K to 423K, and the extreme temperature zone environment required by deep space exploration including the lunar surface polar zone and the Mars can be completed; meanwhile, the integrated heat exchange cryogenic subsystem based on heat conduction and convection is compact in structure, liquid nitrogen and liquid helium do not need to be used, and energy conservation and environmental protection are achieved.

The invention discloses an installation method for mounting a large-aperture microwave antenna on an optical antenna, and relates to the field of spaceflight deep space exploration. The method comprises the following steps: firstly, welding a mounting steel plate in a microwave antenna center body, forming a hole in an antenna panel, then integrally hoisting an optical antenna and an adjusting bracket into the microwave antenna center body through a hoisting device, and mounting the optical antenna and the adjusting bracket on the mounting steel plate; and finally, the angle of the optical antenna is adjusted through the adjusting bracket, and a cable is arranged. The installation mode is simple, the structure is stable, and the electric axis of the microwave antenna and the optical axis of the optical antenna can be adjusted to be consistent. According to the invention, the microwave antenna can be upgraded and reformed, and a composite structure of the optical antenna and the microwave antenna is realized.

The present invention discloses a robust optimization method for autonomous optical navigation landmarks for planetary landing, which belongs to the field of deep space exploration technology. The implementation method of the present invention is as follows: using the height information of the lander to determine the scale of the image plane projected onto the planetary surface, and deriving the quadrilateral vertex expression of the field of view based on the geometric relationship; using the relationship between the field of view vertex deviation and the lander posture error, converting the posture uncertainty to the field of view vertex uncertainty, and using the error ellipse to describe the field of view vertex uncertainty distribution; screening the quadrilateral area formed by the intersection of common tangents, which is the field of view intersection under the lander posture uncertainty; using the nominal trajectory and camera parameters to estimate the field of view sequence, combining the field of view intersection acquisition method to obtain the field of view intersection sequence, the field of view intersection sequence is obtained by offline estimation, and the amount of onboard calculation of the lander is reduced; using the observability of the navigation system to establish the landmark optimization index, optimize the selection of the landmarks in the field of view intersection sequence, and reduce the influence of posture uncertainty on the selected landmarks.

The invention discloses a lunar scientific research station micro-grid system based on a multi-source access electric energy router, and belongs to the technical field of deep space exploration and micro-grid energy supply systems. The micro-grid system comprises a medium-large micro-grid and a plurality of small micro-grids, and the medium-large micro-grid takes a high-voltage alternating-current backbone network as a framework and is connected with the small micro-grids; each micro-grid comprises a plurality of electric energy routers, and the electric energy routers are connected in parallel through high-voltage alternating-current ports; the electric energy router is connected with various distributed power supplies through a plurality of ports, supplies power to a load, and is responsible for scheduling and managing multi-source energy; and each small micro-grid performs micro-source configuration and port and capacity configuration of the electric energy router according to the load and in-situ resource characteristics of the power supply area of the small micro-grid. A quasi Z source converter and high-frequency transformer technology is adopted to realize cross-voltage-level energy efficient conversion, the flexibility and robustness of an energy system are remarkably improved, and theoretical support and engineering reference are provided for all-weather autonomous operation of a lunar scientific research station.

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 point cloud registration method based on target sailboard features. In order to solve the problem of registration error accumulation when low-overlapping-rate sparse point clouds are processed under the condition of resource limitation in the prior art, the invention provides the following improvement schemes: firstly, designing a preprocessing module in which multi-scale statistical outlier detection and radius filtering local smoothing processing are coordinated, so that the noise point filtering rate is improved to 92% or above; secondly, a weighted PCA coordinate system construction method constrained by an axial bounding box (AABB) is innovatively provided, and the fitting precision of the coordinate system is improved by 40% through a weighted fusion strategy of a covariance matrix; and finally, constructing a registration evaluation function for verifying geometric consistency based on key points, and effectively eliminating mismatching caused by symmetric ambiguity in combination with an improved RANSAC algorithm. Experiments show that the method can still keep the registration success rate of 89.7% when the point cloud overlapping rate is lower than 30%, and the registration error is reduced by 62.5% compared with a traditional ICP algorithm. The method is especially suitable for non-cooperative target three-dimensional reconstruction in resource limited scenes such as deep space exploration, and provides reliable technical support for on-orbit service of spacecrafts.

The invention relates to the technical field of deep space exploration, in particular to a cryogenic propellant on-orbit low-loss storage system and method for a deep space probe. After the low-temperature propellant is injected into the storage tank through the injection pipe, along with continuous accumulation of external leaked heat, the first pressure sensor detects that the pressure in the storage tank is continuously increased, and when the numerical value of the first pressure sensor exceeds the preset pressure, the cooling assembly is started to cool the low-temperature propellant in the storage tank, so that the external leaked heat is consumed; before the engine needs to supply the low-temperature propellant, the low-temperature propellant in the storage tank is in a supercritical state, and the storage temperature is increased in a high-pressure storage mode, so that the temperature difference between the storage tank and the outside and the heat leakage amount are reduced, and the requirement for the refrigerating capacity of the cooling assembly is reduced; when the low-temperature propellant is conveyed, due to the fact that the low-temperature propellant is in a supercritical state and free of gas-liquid phase separation, the interior of the whole storage box is in a homogeneous state, the stable conveying flow of the low-temperature propellant can be guaranteed, and stable output of an engine is also facilitated.

The invention relates to the technical field of deep space exploration visual three-dimensional terrain reconstruction error analysis, in particular to a visual three-dimensional terrain reconstruction error modeling method and system for a Mars patroller. In view of the limitation of the Mars surface environment and the existing error analysis method, the purpose of improving the three-dimensional reconstruction precision is achieved. Technically, the method comprises the following steps: sparsely reconstructing a covariance propagation model based on bundle adjustment, processing a camera imaging equation, carrying out re-projection error calculation and optimization, carrying out nonlinear least square algorithm iterative solution and the like to obtain a camera attitude, a three-dimensional point position parameter and a covariance matrix of the three-dimensional point position parameter; densely reconstructing a covariance propagation model based on linear triangularization, and calculating a three-dimensional point coordinate covariance matrix through equation conversion, least square solution and covariance propagation formula derivation. The experiment simulates the Mars environment to obtain simulation data for dense reconstruction error analysis, and the result shows that the method can effectively analyze errors, significantly improve the three-dimensional terrain reconstruction precision, and powerfully guarantee Mars detection and navigation tasks.

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 invention relates to a pathfinder test satellite suitable for a deep space exploration flight mission, and the satellite orbit of the pathfinder test satellite is a non-near earth orbit which avoids the influence of a normal Airy radiation band, and is a low orbit inclination angle which is free from the influence of strong space radiation. The method has the beneficial effects that the satellite orbit is not influenced by the Nabelian radiation band and is consistent with the actual deep space orbit environment.

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 discloses an interference time delay observed quantity acquisition method and system applied to a small-bandwidth signal, and relates to the technical field of deep space exploration, and the method comprises the steps: designing a signal frequency band broadening factor corresponding to a transmitting signal of a spacecraft; constructing a time delay model based on a baseline; based on the signal frequency band broadening factor, correcting the baseline-based time delay model to obtain a target time delay model; and calculating interference time delay according to the target time delay model. According to the method, the interference time delay of the spacecraft which does not have a special radio beacon and only emits a small-bandwidth signal can be determined, and the method has a relatively high application value.