14 results about "Space probe" patented technology

1. The name of the design product: Launch Vehicle (Chirei 6). 2. The use of the design product: used for space transportation, sending the payload such as artificial earth satellites, manned spacecraft, space stations or space probes into the predetermined space orbit. 3. The design points of the design product: the combination of shape, pattern and color. 4. The picture or photo that best shows the design points: perspective view. 5. The design claimed contains color.

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.

The invention provides an observability analysis method and device for deep space exploration optical autonomous navigation, and the method comprises the following steps: constructing an orbit dynamics model and an optical observation model according to the measurement information obtained by a deep space probe; constructing an optical autonomous navigation system model according to the orbit dynamics model and the optical observation model; observability parameters of the deep space exploration optical autonomous navigation system are given according to the optical autonomous navigation system model; constructing an observability characterization model of the autonomous navigation system; carrying out dimensionality reduction characterization on observability of the deep space exploration optical autonomous navigation system; therefore, an observability criterion is obtained; and realizing the observability autonomous determination of the deep space exploration optical autonomous navigation system according to the observability criterion. By analyzing key factors of complete representation of the observability of the system, judgment conditions of the observability of the system are deduced, and the observability quantitative expression method which is universal, simple and easy to autonomously realize on a satellite is provided.

The invention discloses a minimum number management system for deep space probe resource limitation. The minimum number management system comprises a processing module and a power distribution module which are located in a reentry capsule, wherein the power distribution module is responsible for supplying power to electronic equipment in the cabin and completing primary power supply combination, primary power distribution and control of a heater safety switch and a grounding switch; the power distribution module receives primary power input in the detectors or between the detectors, outputs primary power distribution to the inward processing module, and outputs primary power distribution and instruction power to other terminals in the detectors. Meanwhile, a safety switch of a heater control circuit of the processing module is controlled, and local state telemetering is externally output for inter-device state monitoring; the processing module receives the primary power supply input of the power distribution module and realizes secondary power supply conversion and power distribution; bus instruction input among detectors or in the detectors and external analog quantity, temperature quantity and passive switching quantity input are received, control instructions are output after logic processing, and data management and autonomous management are achieved at the same time.

[Problem] To provide novel features. [Solution] One aspect of the present invention sets forth a Hall thruster provided with an anode, a vaporization chamber, and a passage formation part. The anode is configured to supply a propellant to a predetermined position in order to generate a propulsive force. The vaporization chamber is configured to vaporize the propellant on the inside thereof. The passage formation part forms a first passage, a second passage, and a third passage. The first passage is configured to guide the propellant to the inside of the vaporization chamber. The second passage is configured to guide, of the propellant having been guided to the vaporization chamber, a predetermined amount of the propellant to the anode. The third passage is configured to guide, of the propellant having been guided to the vaporization chamber, the propellant other than the predetermined amount to the outside of the Hall thruster.

This invention discloses a hierarchical matching pose estimation method for optical navigation landmarks in deep space probes, belonging to the field of autonomous navigation technology for deep space exploration. The implementation method is as follows: A probe pose dynamics model and an optical observation model are established to obtain the probe's initial position, attitude, and camera parameters, used to predict the probe's state and the set of visible landmarks at the observation time; a navigation landmark observability index function is constructed based on the Fisher information matrix; a hierarchical landmark selection and matching strategy is constructed, considering landmark visibility constraints, and selecting a primary landmark set, a secondary landmark set, and a candidate landmark set from the visible landmark set at the observation time based on the probe's trajectory and the set of visible landmarks at the observation time; sequential matching is performed during online matching to suppress the decrease in navigation information caused by landmark matching loss; and step-by-step matching is used during probe navigation to achieve rapid landmark identification and high-precision pose estimation.

This invention discloses a low-gravity simulation servo control method and apparatus for deep space exploration landing experiments. The method includes: acquiring the structural parameters of the low-gravity simulation test platform and establishing a spatial structural model of the parallel cable drive system based on the structural parameters; establishing a force-displacement characteristic model of the parallel cable drive system based on the spatial structural model, and obtaining mapping relationship data between platform displacement data and cable tension data based on the force-displacement characteristic model; acquiring the motion trajectory data of the deep space probe during the landing process, determining the target servo trajectory of the servo platform based on the motion trajectory data, and calculating the target cable tension data required to achieve the target servo trajectory based on the mapping relationship data; and controlling the drive device in the parallel cable drive system to adjust the tension of each cable based on the target cable tension data to drive the servo platform to move according to the target servo trajectory. This invention solves the technical problem of poor servo platform control performance in the prior art.

The invention relates to a space probe (2) with optimized thermal management for operation in extreme environments as encountered on the moon, the space probe comprising a chassis (4) to receive probe components, four wheels (10) attached to the chassis and a mobile body (14) assembled on the chassis, the mobile body comprising a wheel shield (16) movable between an open position in which the wheels are exposed and a closed position in which the wheels are covered, and an access hatch (18) movable between an open position in which at least some components of the probe are exposed and a closed position in which at least some components of the probe are received inside the body. The body is movable relative to the chassis between a high rolling position in which the body is elevated relative to the wheels and a low receiving position in which the body is lowered relative to the wheels to increase the receptiveness of the probe components so as to limit heat losses.

1. Name of the product in this design: Launch Vehicle (Chitu 6A). 2. Purpose of this design: For use in space transportation vehicles to send payloads such as artificial Earth satellites, manned spacecraft, space stations, or space probes into predetermined space orbits. 3. The key design elements of this product are the combination of shape, pattern, and color. 4. The image or photograph that best illustrates the design's key points: a 3D model. 5. The design for which protection is sought includes color.

This invention discloses a robust tracking control method for flexible attachment trajectories on small celestial bodies, belonging to the field of deep space probe control technology. The implementation method is as follows: While retaining the flexibility characteristics, the structure of the flexible probe is simplified. A "spring-damping-torsion spring" model of the flexible probe is established in both the flexible node reference coordinate system and the node fixed coordinate system, enabling it to possess both flexibility and, as far as possible, effectively estimate and control the state of its attachment process. A nominal trajectory error tracking control model is established based on the dynamic model. A performance index function is designed to transform the flexible probe attachment trajectory tracking control problem into an optimal problem. An HJB equation is established based on the performance index function, and the expression for the optimal control force is calculated. Through strategy iteration, the control law and performance index function are formed into a closed-loop equation. A single-evaluation neural network is used to approximate the optimal control law and optimal performance index function, achieving robust tracking of the nominal trajectory while reducing probe fuel consumption.

This invention provides an internal communication management system for a deep space exploration satellite, belonging to the field of communication transmission technology. It includes a communication management unit, a satellite integrated electronic subsystem, and multiple payloads. The communication management unit connects to the satellite integrated electronic subsystem via a 1553B bus and connects to each payload via an RS422 bus and a SerDes bus, respectively. The link layer of the communication management unit responds to data block transmission commands received via the 1553B bus, dynamically switching between master-slave mode and point-to-point mode. In master-slave mode, it polls multiple payloads; in point-to-point mode, it establishes a direct link with a designated payload to transmit scientific data. The command layer organizes mission commands into command frames and sends them to the payloads, parses the response frames returned by the payloads, and interacts with the satellite integrated electronic subsystem via data frames. While the SerDes bus is transmitting data in point-to-point mode, the communication management unit suspends response to all commands except for reset commands until the current data transmission is complete.

The invention discloses a deep space probe energy management strategy design method, which comprises the following steps of: during electric propulsion work, executing a whole device energy safety strategy according to a logic sequence of electric propulsion power supply unit under-voltage protection, power supply controller fixed working point protection and whole device platform energy safety protection in sequence; and when the electric propulsion does not work, the whole device energy safety strategy is executed according to the logic sequence of power supply controller fixed working point protection and whole device platform energy safety protection. According to the invention, the energy safety of the deep space electric propulsion detector in the flight stage is ensured.

The invention discloses a GaAs three-junction cell neutron irradiation joint simulation method based on Geant4 and TCAD, distribution of parameters in a cell is accurately calculated through joint simulation, the distribution is combined with experimental results, a solar cell neutron radiation damage evaluation method is analyzed and improved, and theoretical support is provided for space application of the solar cell neutron radiation damage evaluation method. According to the method, Geant4 and TCAD joint simulation is used for replacing a traditional ground neutron irradiation test, the evaluation period can be remarkably shortened, and the test cost can be reduced. Different fluence and structure parameters can be iterated repeatedly through one-time building of the model, the solar cell on-orbit performance boundary is locked in advance, later reworking and scheduling waiting are reduced, satellites, deep space probes and nuclear power system suppliers are helped to complete reliability verification in the scheme stage, and cost can be reduced continuously and efficiency can be increased continuously.

1. Name of the designed product: Launch Vehicle (Chishui 1). 2. Use of the designed product: used for space transportation, sending payloads such as artificial satellites, manned spacecraft, space stations or space probes into the predetermined space orbit. 3. Design points of the designed product: the combination of shape, pattern and color. 4. Picture or photo that best shows the design points: perspective view. 5. The design for which protection is sought includes color. 6. Other circumstances that need to be explained: the reference view is the main view in the state of lowering the bottom support.