Advances in Astronautics Science and Technology最新文献

Aiming at the electrostatic discharge characteristics of space high-voltage power system, a discharge detection technology based on fluorescent fiber is proposed. The optical signal generated by the electrostatic discharge is received by the fluorescent fiber, and then converted into an electrical signal through photoelectric conversion to realize the electrostatic discharge detection. The electrostatic discharge ground experimental system was built, and the analysis of different design parameters of the sensor through experiment was carried out, and the optimal design parameters were selected. Based on it, the electrostatic discharge detection experiment by fluorescent fiber sensor was carried out. The experimental results show that the developed fluorescent optical fiber sensor can quickly and accurately detect the electrostatic discharge signal.

The in-orbit network observation and data recording and playback of Fengyun-3 is limited by the configuration of domestic ground stations and the Antarctic station, which may potentially affect the integrity and timeliness of global data reception. This paper expounds the autonomous program control design of global data recording and playback of FY-3E satellite and the efficient data processing and transmission process, establishes a data timeliness simulation analysis model and analyzed the timeliness of payload data acquisition under different strategies of data playback toward Antarctic station. The analysis results and experimental verification show that the integrity and timeliness of global data acquisition can be ensured by optimizing the use frequency of the Antarctic station.

Since the navigation sensors used in angles-only navigation are simple, angles-only navigation will be a critical enabling technique for spacecraft autonomous rendezvous and docking (AR&D). This paper reviews the angles-only navigation technique for spacecraft AR&D, including the concept, application analysis, on-orbit verification, current status, and future development trend of angles-only navigation technique. The current status, inadequacies, and questions for further study of four research methods in angles-only navigation technique are summarized, including nonlinear dynamics method, multi-satellite multi-sensor method, orbital maneuver method, and camera offset method, which provide new ideas and directions for the engineering application and academic research on angles-only navigation technique.

This article summarizes the composite honeycomb structure which possess important meaning and application value on the high-precision satellite antenna reflector. The key technologies of composite material honeycomb structure are summarized, including the material selection for satellite antenna reflector, honeycomb configuration, fabrication process, mechanical properties, lightweight design, surface accuracy, thermal deformation control and other issues. The development goal of “lighter, larger, more refined and more stable” are put forward after looking forward to the manufacturing technology and functional requirement of the future satellite antenna reflector.

High-resolution observation requires the design of space telescopes with larger and larger aperture. Larger but not heavier deployable sunshields are essentially needed. Due to the advantages such as smaller storage volume and lightweight, the membrane structure can meet the demanding requirements of the design of larger membrane sunshields and has gradually become a current research hotspot. This paper summarizes the research progresses of sunshield deployment technology from three categories: mechanically driven deployment, elastic deployment, and inflatable deployment. The folding methods of membrane sunshields with different geometric shapes are compared, and the research status of membrane folding technology is summarized. The summary gives some suggestions on future sunshield deployment and folding technology.

This paper introduces the lightweight thermal protection system (TPS) of The Chinese Mars probe Tianwen-1. The aerodynamic environmental conditions and important design elements are described and analyzed. The design idea, design scheme, analysis and experiment of the thermal protection system are mainly discussed.

Fengyun-3E(FY-3E) satellite is the first early morning orbit meteorological satellite for civil use in the world. It operates in the sun-synchronous orbit whose nominal altitude is 836 km and local time of descending node is 05:30–05:50. It is equipped with eleven payloads, which can realize comprehensive detection of various spectral bands from extreme ultraviolet, ultraviolet, visible, infrared to microwave. All-band absolute radiometric calibration in orbit has been realized on FY-3E satellite, with the calibration error of infrared band up to 0.4 K, microwave band up to 0.8 K, and visible near-infrared band up to 5%. FY-3E satellite can provide images, clouds and radiation, atmospheric parameters, sea and land surface, space weather and other products, which are important supporting data for weather forecast, climate monitoring and environmental disaster monitoring. This paper introduces the system design scheme of FY-3E satellite, summarizes the main technical features of the satellite, and looks forward to the application prospect of the satellite.

Chinese library classification number: V411.8; TP391.9

Document identification code: A

Due to the high specific strength and specific stiffness of the lattice structure, it has been widely used in aerospace and other fields. Aiming at the lightweight requirements of spacecraft, a research on the lightweight design of the pressurized structure is carried out based on lattice truss sandwich. An axisymmetric cell structure and arrangement method is proposed, which can improve the structural bearing efficiency under internal pressure load, reduce the structure weight and ensure the consistency of deformation. At the same time, the influence of the parameters of the lattice sandwich structure on the performance of the structure is analyzed by numerical simulation. The size effect of the pressured structure is analyzed, and the equivalent methods for different structures are evaluated. The calculation results of the equivalent model are verified, and the results are proved to be credible, which can greatly reduce the computational cost and time to meet the requirements of engineering applications.

Taking complex spacecraft shell structure containing local small features (such as support, assembly interface, stiffener, etc.) as the object. From the perspective of average, considering the leakage and disturbance of elastic wave propagation caused by local small features on the surface. Based on the fact that the energy path required for elastic wave propagation from one source to any other point on the structural shell is the smallest, a method of impact location using time history data is proposed. A simulation example of typical impact event location of pressure storage tank is given. The results show that the positioning error obtained by this method can meet the defined engineering requirements (0.5 m) for the disposal of impact events, and has a certain engineering reference value for the positioning of complex spacecraft structure cabin impacted by space debris.

This abstract proposes a design that helps analyze the causalities experienced by a spacecraft during communication loss or any unpredicted event. The idea is to build a mini backup box akin deployable spacecraft unit, also called a Redundant Unit that gets deployed under the command of the central unit on the occurrence of any possible danger to the spacecraft. This deployed unit ensures to picture and measure the spacecraft parameters at the time of deployment and store the data within it. This unit also serves the purpose of storing the backup payload data of a spacecraft under an uncompromisable fate. This helps in learning the potential dangers for a spacecraft alongside preventing the complete loss of mission data during any causality. This paper propounds the overall design of the structure and internal architecture of the Redundant unit with all the required subsystems, and technologies involved. The deploying mechanisms, payloads of the redundant unit, and methods employed will be presented on the basis of the most common possible fates for spacecraft.