Advances in Astronautics Science and Technology最新文献

This article presents the systematic design process for a low-cost 6U CubeSat platform, drawing on the experience of the highly motivated Pluto team. The team's success in a national academic CubeSat design competition led to the establishment of a space startup and the decision to develop a 6U platform. The primary motivation for writing this research is to increase access to space and space services by helping startups _especially in underdeveloped countries, design and build a CubeSat with the least cost and effort in the shortest possible time. In the design process, simplicity, reliability, and the possibility of reproduction at the lowest possible cost have been prioritized. Aligned with ECSS standards tailored for CubeSats, the design method parameters of the 6U platform are thoroughly examined. The article highlights the development of a state machine and the justification of design requirements through standard methods and tracking them using RTM and RVTM tables. Effective interface control while using COTS components is emphasized to reduce costs by approximately 50% while ensuring quality and meeting space environment requirements. The architecture of the Pluto platform, comprising entirely of commercial components, is showcased, providing insights into its system characteristics. This systematic design underscores the importance of modularity, affordability, and utilization of COTS components. By sharing their experiences, the Pluto team aims to support space industry startups and inspire innovative CubeSat projects.

International cooperation in commercial space is an effective way to optimise the space industry and maximise the interests of all parties. China’s commercial space industry started relatively late, and China is also actively seeking cooperation. However, some developed countries, including the United States, have strictly controlled the export of space-related goods, technology and services through Missile Technology Control Regime, the Wassenaar Arrangement and related domestic laws. In addition, China’s export control regulations related to the space industry are scattered and lack unified applicable rules, which is not conducive to potential commercial space internationalisation. China needs to establish a comprehensive, scientific and practical legal regime and policy support mechanism for the export control of space-related items. Meanwhile, China should participate more in the international multilateral export control system and break through the bottleneck of international cooperation in commercial space through transparency, mutual trust and reciprocity.

Currently, low-orbit mega-constellations have been fully utilized in military applications, but the standards for using them as military targets are still lacking, and international legal provisions are ambiguous. Existing theories are also unable to clearly define and distinguish the military applications of low-orbit mega-constellations. Whether low-orbit mega-constellations can be used as military targets should be considered from two aspects: whether they violate the principle of neutrality and whether they belong to weapon systems. Since the majority of the holders of mega-constellations are currently private space companies, which are not subjects of international law, the application of the principle of neutrality should be analyzed based on the impact of private company behavior on the neutrality of non-directly belligerent states. Regarding whether low-orbit mega-constellations belong to weapon systems, it should be observed from different application scenarios of mega-constellations and compared with the definition of weapon systems to ultimately define the boundary conditions for whether low-orbit mega-constellations belong to weapon systems in different scenarios.

Structural tests are to gain confidence in the analytical predictions that support spacecraft development, and ultimately to support the qualification and flight acceptance of the spacecraft system. Based on envelopes of real-time launch vehicle data or simulation results, the input level of the vibration test is calculated with a certain safety margin. This conventional approach to vibration test may lead to over-testing problems, which will severely harm the spacecraft at resonance frequencies. To elaborate on the appropriate force input, Multiple DOF dynamic interface forces during the lift-off must be measured. The force sensor, which should be placed between the spacecraft and launch vehicle, is apparently not a good strategy, because it changes the connecting stiffness and strength of the interface between spacecraft and launch vehicle. Accordingly, a novel identification method for dynamic interaction force, based on the strain status of the spacecraft adapter ring, is proposed in the current study. Some special observation locations are selected along the surface of the adapter ring, on which strain rosettes are pasted to measure the local normal and shear strain. During the lift-off, the telemetry strain signal will be gathered to estimate Multiple DOF forces by theoretical analysis combined with ground test results. It is a promising method for future application.

Projects concerning space are hugely valuable to our species. Two notable physical districts are (a) the various orbits local to earth and (b) areas that are more remotely located in the interplanetary and interstellar regions. However, the legacy of decades of human space observation, exploitation, and exploration has not always been positive. Environments have been impacted and key groups have been inconvenienced and even their safety threatened due to the ventures of some actors. If such activity continues, the damage caused to our societies, our local space, and even our outer space might become irretrievable. This paper calls for actors to work with their fellow earthlings to identify and address the negative consequences of space endeavours prior to their eventuation. By employing notions of long-view sustainability, we may visualise how our projects affect not only the environment, but also us, and the legacy that we leave for our future generations.

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.