Against the backdrop of the rapid development of global low-orbit constellations, highly efficient and reliable propulsion technology has become key to large-scale deployment. Electric propulsion systems are the preferred choice due to advantages such as high specific impulse and low cost. Among them, the permanent magnet Hall thruster, characterized by its zero quiescent power consumption, high reliability, and compact structure, is emerging as the mainstream technological approach for low-to-medium power applications. This paper systematically compares the characteristics of both permanent magnet and electromagnetic excitation technical schemes, with a focus on the performance evaluation of a magnet Hall thrusters batch-applied for the first time in a major domestic constellation, based on ground and in-orbit data. Analysis of long-term telemetry data indicates stable thruster operation and good consistency in key parameters, successfully fulfilling orbital control tasks and verifying its long-term reliability in the actual space environment. This study provides substantial data support and engineering reference for the selection and design of propulsion systems in subsequent Chinese low-orbit constellations.

Driven by the global commercial space wave, remote sensing constellations are accelerating their transformation towards ultra-large-scale deployment and multi-scenario market-oriented applications. Traditional simulation tools face prominent problems such as high model coupling, poor scalability, single scenario adaptability, and lack of commercial effectiveness quantification capabilities, making it difficult to support constellation design demonstration and operational decision-making. To address these issues, this paper focuses on the construction method of a large-scale multi-scenario space remote sensing satellite simulation system, and proposes and implements an integrated, high-fidelity, and scalable simulation platform. A four-layer architecture of “Application Layer - Task Layer - Service Layer - Basic Support Layer" is innovatively designed to break through the bottleneck of ultra-large-scale constellation simulation. An integrated modeling method combining component-based and parameterized approaches is adopted to realize flexible reuse and rapid configuration of core components such as satellite platforms and optical/synthetic aperture radar payloads. A multi-scenario driving mechanism based on standardized configuration files is constructed to support one-click switching of diversified scenarios including commercial mapping and agricultural monitoring. Based on the core logic of "mission-driven-resource collaboration - data closed-loop”, the complete link from mission analysis, resource scheduling to data output is connected, and commercial effectiveness indicators such as task completion rate and resource utilization rate are quantified. Simulation results show that the system can effectively support the simulation verification of constellations with a scale of 50~10 000 satellites, compared with the modeling cycle of traditional equipment systems (usually 1~2 months), the modeling cycle of the system can be shortened to within 1~2 days, significantly reduce the development risk and operational cost of commercial constellations, and improve the market response speed. The research in this paper provides key technical support for the digital construction, mission planning optimization and effectiveness evaluation of China’s ultra-large-scale commercial remote sensing constellations.

Aiming at the phenomenon of overly conservative flight load design results in the high-wind zone of traditional launch vehicle design methods—caused by factors such as the use of statistical high-altitude wind fields, independent work across departments, and repeated consideration of parameter deviations across disciplines—this paper proposes a probabilistic flight load design method for the high-wind zone based on measured high-altitude wind data. This method integrates wind-compensated trajectory design, six-degree-of-freedom Monte Carlo simulation, active load alleviation, and load synthesis techniques to provide flight loads experienced by various structural sections of the launch vehicle in the high-wind zone. These loads are derived from historical measured wind field data and satisfy a certain probability threshold. The advantages of this method lie in its direct use of measured high-altitude wind data, avoidance of repeated parameter deviation considerations, and integration of trajectory wind compensation and active load alleviation technologies. This technology has been successfully applied to the pre-launch quasi-real-time wind compensation for the ZQ-2EY2 launch vehicle, as well as the high-wind zone flight load design for the ZQ-3 launch vehicles. It has effectively increased the launch-day high-altitude wind clearance probability for the ZQ-2EY2 and significantly reduced the high-wind zone flight loads for the ZQ-3, thereby lowering structural weight and improving launch vehicle performance.The application of this technology effectively enhances the launch vehicle's payload capacity and adaptability to complex meteorological conditions. It provides greater possibilities and opportunities for space exploration, driving the advancement of space science research and experimentation.

On May 29, 2025, The Tianwen-2 probe had been successfully launched, embarking on the China’s first asteroid and comet exploration mission. With a single launch, the mission aims to achieve sample return from asteroid 2016 HO3 and fly-by detection of comet 311P. The Asteroid Medium Angle Camera (AMAC) is one of the key optical payloads carried on the probe, designed for global imaging of asteroids. It is expected to determine physical parameters such as rotation characteristics, shape, and size of asteroids and main-belt comets, as well as study their surface morphology and other scientific objectives. This paper introduces the scientific objectives, functions, and performance specifications of the AMAC. It provides a detailed overview of the camera’s optical system design, structural design, electronics design, and FPGA software design. Additionally, the calibration tests, ground verification experiments, and their results are discussed. Currently, the camera has completed its first in-orbit imaging session, capturing some color images of earth and the Earth-Moon system. The output images are clear with accurate color reproduction.

On-orbit maintenance is crucial for ensuring the long-term operation of electronic equipment, and welding is an indispensable part of precision maintenance tasks for orbital electronic systems. However, the harmful gasses volatilized during soldering paste heating in space pose a serious threat to the sealed cabin environment. To address this challenge, this paper presents the design of an intelligent harmful gas purification system specifically tailored for the orbital environment. By developing a three-stage purification architecture leveraging microgravity fluid dynamics and innovative mechanical design, the system integrates mechanical filtration, harmful gas adsorption, and catalytic oxidation modules. A circuit control system was designed to enable intelligent regulation of the purification process. A three-dimensional transient simulation model was established using the COMSOL Multiphysics platform to validate the system’s purification performance under typical space station conditions. Results demonstrate that the system forms stable airflow paths driven by fan-induced negative pressure, achieving high efficiency in waste gas treatment. The close agreement between calculated and simulated results further verifies the rationality and accuracy of the model, providing a reliable simulation basis for the design and optimization of harmful gas purifiers in practical engineering applications.

As deep space exploration missions progress and lunar base construction advances, in-situ lunar water ice extraction technologies have become pivotal for achieving resource self-sufficiency, reducing transportation costs, and supporting long-term lunar habitation. The permanently shadowed regions at the lunar poles are considered the most promising areas for water ice accumulation. However, the efficient extraction of water ice remains a significant challenge due to factors such as the extremely low thermal conductivity of lunar regolith, sublimation losses in the vacuum environment, and the formation of insulating layers. This paper provides a comprehensive review of the physical mechanisms governing the sublimation behavior of lunar water ice and the associated experimental simulation techniques. It also outlines the current state of in-situ heating extraction methods, including insertion heating, microwave heating, and solar heating, while highlighting the research progress and application potential of these approaches. A particular focus is placed on the impact of sublimation delay effects on extraction efficiency, with discussions on low-temperature isothermal heating strategies, the coupling of ice grain size with thermal field models, and the optimization of equipment layout. Based on this review, the paper offers insights into the future development trends of in-situ resource utilization systems for the Moon and emphasizes the need for enhanced coupling models of sublimation behavior with the actual properties of lunar regolith, as well as validation through ground-based environmental simulation experiments. These efforts are essential for advancing water ice extraction technologies toward greater efficiency and sustainability.

Asteroid monitoring technology forms a cornerstone in the effort to foster a community with a shared future for mankind against asteroid threats. Conducting in-depth research on near-Earth asteroid (NEA) monitoring technologies is essential not only for safeguarding human development and survival but also for establishing independent decision-making authority in critical global security events and assuming a voice and leadership role in international space affairs. This paper offers a comprehensive analysis of the hardware components, detection objectives, mission scenarios, operating modes, scientific contributions, technical characteristics, and highlight features of major foreign ground-based and space-based monitoring systems. Based on this assessment, it identifies future development trends in asteroid monitoring. Additionally, in light of the current state of development in this field in China, the paper provides systematic recommendations focusing on top-level design, technological layout, scientific development, mission execution, and international cooperation. These recommendations aim to serve as a reference for China’s effort to address NEA impact risks and enhance its NEA monitoring capabilities.

Recovering the test model is important in developing the techniques of measuring the parameter continuously and directly during its flying process on the ballistic range. It is more difficult to recover the test model with hypervelocity on the ballistic range with the increase of flying velocity and mass, and the requirement is much higher for the design of test model and recovery system. Soft recovery techniques were studied for the test model with launching velocity above 3.0 km/s on the ballistic range. The design requirement for the test model and sabot was summarized in order to ensure the model integrity during its deceleration and recovery process. The design method of shielding heat was summarized in order to protect the data storage components installed in the test model. The deceleration and recovery system was also designed. The intact free-flight model was recovered safely with a mass of 837 g and a launching velocity of 3.3 km/s, and the whole measurement data from onboard diagnostics were obtained, i.e. the acceleration, external pressure and temperature during the process of launching, flying and recovery. Based on the measuring requirement of aerodynamic force and the development of soft recovery techniques, the test method of recovering the model softly and using repeatedly was proposed on the ballistic range.