8 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.

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.

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.