10 results about "Nano satellite" patented technology

A kind of micro-nano satellite module rapid integration method belongs to the field of relay satellite platform, there is standardization backplane and standardization module, standardization backplane is provided with bus area and slot area, bus area includes uniform specification power bus and data bus, slot area is arranged with multiple standardization slots, standardization module is inserted into standardization slot.The structure of standardization slot is uniform, and a uniform standard data electrical interface is provided inside, each standardization slot corresponds to fixed physical port and logical address / node number, or unified address configuration is realized through slot coding, according to functional task requirement, select the standardization module that meets functional task requirement, and build the satellite system that meets functional task requirement.The present application significantly shortens the development cycle, greatly reduces the development cost, greatly improves the system flexibility and scalability, improves the system reliability and maintainability, and promotes standardization and industrialization.

This invention relates to a method, system, and device for dynamically adjusting the protection threshold of a micro / nano satellite battery, belonging to the field of power management technology. The method includes: real-time acquisition of voltage, current, and temperature parameters; real-time estimation of the health status value of each individual battery cell based on the acquired voltage, current, and temperature parameters; using the estimated health status value as a query index to query a preset mapping table between health status and protection thresholds to obtain a dynamic protection threshold for at least one protection type corresponding to the current health status value; comparing the voltage, current, and temperature parameters with the dynamic protection thresholds respectively to determine if any parameter exceeds the corresponding dynamic protection threshold; and executing a preset battery protection action when any parameter exceeds the corresponding dynamic protection threshold. This invention can sense the battery's own health status and adaptively adjust the protection threshold according to its aging degree.

The application discloses an on-orbit use method of a green single-component thruster, and the single-component thruster structure comprises five parts of an injector, an anti-inversion functional material, a catalytic bed, a nozzle and a thermal control assembly, wherein the thermal control assembly comprises an armored heater, an armored thermistor and a multilayer thermal insulation assembly. The application provides the on-orbit use method of the green single-component thruster containing the anti-inversion functional material, and solves the technical problem of the warm start life of the green single-component thruster through reasonable working condition design, and the green single-component thruster is successfully applied to micro-nano satellites.

This invention relates to the field of spacecraft mission planning technology and discloses a method for autonomous mission planning of micro- and nano-satellite reconnaissance based on predictive spatiotemporal heat maps. The method includes: generating a predictive spatiotemporal heat map characterizing the predicted severity and observational uncertainty of a disaster area by fusing multi-source observation data with a disaster evolution physics model through Gaussian process regression of physical information; constructing a rolling temporal control planning model coupled with satellite attitude, energy, and orbital constraints based on the predictive spatiotemporal heat map for each satellite; solving the planning model online using a sequential convex optimization algorithm to obtain the optimal observation mission sequence and attitude maneuver strategy for each satellite; dynamically updating the observation value of the planned area through a shared heat map based on a coverage suppression mechanism, guiding neighboring satellites to automatically turn to unobserved high-value areas to achieve distributed collaborative mission allocation; and updating the predictive spatiotemporal heat map in a closed loop using newly acquired observation data.

The application discloses a kind of remote sensing micro-nano satellite integrated information processing platform, belong to aerospace field, including satellite optical load module, data processing module, image correction module;The satellite optical load module is used to provide load image data to the data processing module;The data processing module is divided into several frame pictures according to preset time period with load image data, then several frame pictures are transferred to image correction module;The image correction module receives several frame pictures and detects, judges whether there is deformation, if there is, it is adjusted, then the picture after adjustment is sent to data processing module;If not, the original picture is sent back to data processing module.The application, by the image correction module set, can delete invalid picture, and then avoid affecting correction accuracy, so as to effectively improve the effect of image detection correction.

The application relates to a production line and assembling method for batch production of stacked micro-nano satellites, and in particular to a production line and assembling method for batch production of stacked micro-nano satellites, which solves the problems of low production (assembling) efficiency, high cost and long cycle of existing satellites, and the method comprises the following steps: single-machine thermal control implementation and sub-assembly assembly to form a single-machine assembly; cabin section assembly to form a complete cabin section module; platform cabin combination to form a complete satellite platform; load cabin docking to form an intermediate state satellite; and solar wing assembly to form a final satellite to be launched. The production line and assembling method for batch production of stacked micro-nano satellites are suitable for batch production of stacked micro-nano satellites.

The device is a DNARNAAvionics (DRAC) ClamSat platform modeled on Biomimetic, Object Oriented (OO) and Internet of Things (IOT) structures. This platform is for controlling the operational aspects of a nano Satellite termed a ClamSat.A ClamSat bi-valve shell uses nano hardware and OO software structures to process solar energy in a biomimetic system characterized by energy storage means. It is operationally managed by OO programs in a DNA / RNA messaging format. The Object-oriented programming (OOP) is a method of structuring a program by grouping related property-es and behaviors into individual objects. The ClamSat OO programs are structured in a class, object, and attribute model of OO DNA / RNA strands within modules will provide interfaces within and across components and subsystems and allow for adaptability and reusability over time. The device communicates wirelessly with a Command-and-Control host infrastructure.The DNA / RNA strand will have Internet of Things (IOT) touchpoints to provide information back to the ClamSat system for Command, Control and Data Handling within the platform.

The present application relates to the technical field of satellite communication, and proposes a micro-nano satellite constellation coordination system and a coordination method, the micro-nano satellite constellation coordination system comprising a multi-modal perception and fusion module, a frequency offset compensation and hybrid communication module, a resource game allocation module, and a lightweight intelligent decision execution module. A Doppler frequency offset compensation mechanism and LoRa+WiFi hybrid networking are introduced, which reduces the inter-satellite link load by ≥40% and the end-to-end delay jitter by ≥30% under equivalent traffic, ensuring the link connectivity rate under high-speed relative motion. Through a lightweight model distillation and quantization scheme, decision reasoning with a delay of <10 ms is successfully realized under the micro-nano satellite computing power constraint of ≤1 TOPS.

The application provides a micro-nano satellite multi-constraint fine control method based on actuator dynamics, and belongs to the field of spacecraft control, and comprises the following steps: considering the electromechanical characteristics of the reaction wheel, an attitude deep coupling model of the micro-nano satellite containing the dynamic characteristics of the reaction wheel is established; aiming at the wheel shaft friction and back electromotive force interference of the reaction wheel, a double interference observer is designed to accurately estimate the wheel shaft friction and back electromotive force interference; aiming at the physical constraints of the satellite rotation speed and the reaction wheel current, a nonlinear state-dependent barrier function is designed to convert the constraint state into a tracking control variable; a composite controller is constructed by combining the double interference observer and the nonlinear state-dependent barrier function, and the high-precision controller design of the micro-nano satellite is completed. The application can overcome the multi-class physical constraint problem in the control of the micro-nano satellite, compensate the interference of the reaction wheel, and has the characteristics of high reliability and high accuracy.