Please help us test our new pre-print finding feature by giving the pre-print link a rating. A 5 star rating indicates the linked pre-print has the exact same content as the published article.
Abstract: Abstract 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. PubDate: 2023-07-17 DOI: 10.1007/s42423-023-00137-9
Please help us test our new pre-print finding feature by giving the pre-print link a rating. A 5 star rating indicates the linked pre-print has the exact same content as the published article.
Abstract: Abstract 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. PubDate: 2023-07-09 DOI: 10.1007/s42423-023-00139-7
Please help us test our new pre-print finding feature by giving the pre-print link a rating. A 5 star rating indicates the linked pre-print has the exact same content as the published article.
Abstract: Abstract 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. PubDate: 2023-07-08 DOI: 10.1007/s42423-023-00138-8
Please help us test our new pre-print finding feature by giving the pre-print link a rating. A 5 star rating indicates the linked pre-print has the exact same content as the published article.
Abstract: Abstract 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. PubDate: 2023-06-15 DOI: 10.1007/s42423-023-00136-w
Please help us test our new pre-print finding feature by giving the pre-print link a rating. A 5 star rating indicates the linked pre-print has the exact same content as the published article.
Abstract: Abstract 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. PubDate: 2023-03-22 DOI: 10.1007/s42423-023-00135-x
Please help us test our new pre-print finding feature by giving the pre-print link a rating. A 5 star rating indicates the linked pre-print has the exact same content as the published article.
Abstract: Abstract The orbital replacement unit and its core technology are the technical basis for the future spacecraft to achieve acceptable on-orbit service and support expansion and upgrading. It can realize on-orbit replacement, replenishment of consumables and other operations, effectively extend the service life of the target spacecraft and maintain the continuity of the mission. In this paper, the mechanical structure of the three-jaw docking interface has been taken as the object and designed the docking interface of the orbital replacement unit which is not mainly dependent on the mechanical arm insertion. The dynamic performance of the docking process was simulated as well. The research work can provide a reference for the design and application of the orbital replacement unit. PubDate: 2022-12-01 DOI: 10.1007/s42423-022-00122-8
Please help us test our new pre-print finding feature by giving the pre-print link a rating. A 5 star rating indicates the linked pre-print has the exact same content as the published article.
Abstract: Abstract Lightweight structures composed of a closed shell and internal lattice infill are highly desirable in satellites on account of their superior specific stiffness and buckling strength, which are brought about by the sandwich effect. These lattice structures can be fabricated by various additive manufacturing techniques, such as selective laser melting (SLM). However, the sub-millimeter-scale shell thickness and lattice strut diameter of the fabricated structure often deviate from the designed dimensions and lead to noteworthy discrepancies between the resonance frequencies of the fabricated structure and those of the initial design model. In this work, a bracket structure for a satellite is designed via topology optimization-based lattice infill approach and fabricated using SLM. A resonance frequency prediction approach based on X-ray micro-computed tomography and the stiffness equivalence is then proposed. Vibration tests are conducted to obtain the resonance frequencies of the fabricated structure. The prediction errors of resonance frequencies for the first three modes are less than 1%, whereas that of the traditional approach based on finite element analysis is as large as 14%. PubDate: 2022-12-01 DOI: 10.1007/s42423-022-00111-x
Please help us test our new pre-print finding feature by giving the pre-print link a rating. A 5 star rating indicates the linked pre-print has the exact same content as the published article.
Abstract: Abstract The dynamic characteristics of a large deployable support arm with uncertain parameters are studied. Due to the processing, manufacturing and other reasons, uncertainty is common in the actual structure, especially for the main bearing structure of high-precision imaging, the uncertainty becomes an important influence that cannot be ignored. In this paper, the modified perturbation method is used to study the change in the structural dynamic characteristics when the elastic modulus of the support arm has a small parameter variation, and the Monte Carlo simulation is used to verify the comparison. The natural vibration characteristics of the support arm structure are measured from the perspective of the statistical characteristics of probability. PubDate: 2022-12-01 DOI: 10.1007/s42423-022-00123-7
Please help us test our new pre-print finding feature by giving the pre-print link a rating. A 5 star rating indicates the linked pre-print has the exact same content as the published article.
Abstract: Abstract Lunar Zebro’s mission is heading the race for deploying the world’s smallest and lightest swarm of nanorovers on the surface of Moon. The concept validation of a single nanorover is of crucial importance, as it will be the launching pad for deploying a swarm of those nanorovers thereafter. Then, they will get connected in a network, acting as a single device and performing scientific missions analyzing data from remote points on the Moon’s surface. In the current study, the complete set of thermo-mechanical-radiation analyses for Lunar Zebro nanorovers are carried out. These range from the Ground Segment to the Moon environment, taking also into account the extreme mechanical and thermal environment at launch-transit conditions when the nanorover is attached to the lander. An innovative ray tracing method to evaluate the effect of the thermal environment on the Lunar Zebro nanorovers is explained in this paper. Material choices, structural design, and mechanical/thermal strategies for the nanorover to overcome the launch, space and Moon’s conditions are shown. The different analyses methods used, expected loads and results obtained should serve as a baseline for evaluating the behaviour of other small devices attached to a lander when aiming for any space mission. More specifically, for those aiming to go to the Moon, the environmental and mechanical expectations here can also be implemented. The ultimate outcome of the paper is the environmental survivability assurance from an analytical perspective of these nanorovers when being sent to the Moon. The validation of the survivability of a single nanorover will be a breakthrough in the space swarm robotics’ field, resulting in the successful performance of the lightest swarm of nanorovers ever deployed on the Moon’s surface. PubDate: 2022-12-01 DOI: 10.1007/s42423-022-00115-7
Please help us test our new pre-print finding feature by giving the pre-print link a rating. A 5 star rating indicates the linked pre-print has the exact same content as the published article.
Abstract: Abstract 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. PubDate: 2022-11-12 DOI: 10.1007/s42423-022-00134-4
Please help us test our new pre-print finding feature by giving the pre-print link a rating. A 5 star rating indicates the linked pre-print has the exact same content as the published article.
Abstract: Abstract 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. PubDate: 2022-09-19 DOI: 10.1007/s42423-022-00132-6
Please help us test our new pre-print finding feature by giving the pre-print link a rating. A 5 star rating indicates the linked pre-print has the exact same content as the published article.
Abstract: Abstract 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. PubDate: 2022-09-05 DOI: 10.1007/s42423-022-00133-5
Please help us test our new pre-print finding feature by giving the pre-print link a rating. A 5 star rating indicates the linked pre-print has the exact same content as the published article.
Abstract: Abstract 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 PubDate: 2022-08-04 DOI: 10.1007/s42423-022-00128-2
Please help us test our new pre-print finding feature by giving the pre-print link a rating. A 5 star rating indicates the linked pre-print has the exact same content as the published article.
Abstract: Abstract 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. PubDate: 2022-07-24 DOI: 10.1007/s42423-022-00129-1
Please help us test our new pre-print finding feature by giving the pre-print link a rating. A 5 star rating indicates the linked pre-print has the exact same content as the published article.
Abstract: Abstract 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. PubDate: 2022-07-13 DOI: 10.1007/s42423-022-00125-5
Please help us test our new pre-print finding feature by giving the pre-print link a rating. A 5 star rating indicates the linked pre-print has the exact same content as the published article.
Abstract: 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. PubDate: 2022-07-13 DOI: 10.1007/s42423-022-00127-3
Please help us test our new pre-print finding feature by giving the pre-print link a rating. A 5 star rating indicates the linked pre-print has the exact same content as the published article.
Abstract: Abstract In this paper, the spectral characteristics, performance of spaceborne radiation source, in orbit infrared radiometric calibration method and radiance data generation process of the Medium Resolution Spectral Imager (MERSI) of FY-3C satellite are introduced. The land surface temperature of typical areas is inversed using the radiometric calibration data. The nonlinear radiometric calibration method for the long wavelength infrared channel with wide spectrum is discussed, the cold space and on-board radiometer count values are obtained independently in each scanning cycle of the instrument, and the infrared channel in orbit calibration calculation is carried out. According to the infrared radiation calibration results, the single channel method is used to retrieve the land surface temperature. The calibration and inversion results provide an important basis for FY-3C/MERSI in orbit performance evaluation. PubDate: 2022-07-12 DOI: 10.1007/s42423-022-00126-4
Please help us test our new pre-print finding feature by giving the pre-print link a rating. A 5 star rating indicates the linked pre-print has the exact same content as the published article.
Abstract: Abstract Ground tests of spacial mechanical products have the characteristics of few test subsamples and expensive test cost, which often appear the cases of zero-failure samples. The classic reliability evaluation methods cannot adapt to the reliability assessment needs of small subsamples and zero-failure samples for high-reliability, long-life spacial complex mechanical products. The characteristics of failure rate functions of typical mechanical products such as mechanical structure, motors, bearings, gears, valves, and so on have been analyzed. Then the reliability evaluation methods of spacial complex mechanical system have been deduced, which has been combined the prior data of Bayesian method. Bayesian posterior distribution function of exponential distribution has been established by the method, which makes use of uniform distribution as a prior distribution, and combines with the convex characteristics of exponential distribution’s failure rate. Bayesian posterior distribution function of exponential distribution has been utilized in products, such as motors, valves, etc., which have characteristics of presenting exponential distribution. The evaluation range of accumulative failure-rate has been reduced by making use of accumulative failure-rate and predicted failure rate of exponential distribution And the weighted least-squares method has been used in parametric fitting based on accumulative failure-rate Then high-precision estimated failure rate of exponential distribution has been obtained. In this paper, the calculation example of compressor filled with spacial propellant has verified the feasibility of the calculation method. The problems of the reliability tests’ few subsamples and evaluating efficiency for expensive, complex spacial mechanical products have been solved effectively by the above proposed method. PubDate: 2022-06-30 DOI: 10.1007/s42423-022-00119-3
Please help us test our new pre-print finding feature by giving the pre-print link a rating. A 5 star rating indicates the linked pre-print has the exact same content as the published article.
Abstract: Abstract The Large Envelope Advanced Parachute System (LEAPS) is developed as a means of recovering the flight data to prove that a student-built sounding rocket, Stratos IV, has reached space. Several design modifications are outlined in this work. The drogue parachute is deployed using a hot gas deployment system to save mass and volume and to increase reliability. The main parachute has been changed to a Disk-Gap-Band parachute as it is better testable in the Open Jet Facility, a subsonic wind tunnel of Delft University of Technology. A heat shield is included to protect the parachute system during atmospheric re-entry. The key benefit of this work is creating a reliable and supersonic parachute recovery system for the safe recovery of flight data located in the sounding rocket's nose cone. PubDate: 2022-06-28 DOI: 10.1007/s42423-022-00098-5
Please help us test our new pre-print finding feature by giving the pre-print link a rating. A 5 star rating indicates the linked pre-print has the exact same content as the published article.
Abstract: Abstract In this paper, a kind of micro–nanosatellite electromagnetic docking device is designed and a configuration of electromagnet with iron-core is proposed. Compared with the coreless coil, the electromagnetic force within the docking range can be significantly increased. To resolve the problem of limited capacity of electromagnet attitude correction, a type of taper hole–taper rod matching mechanism is designed to limit non-docking axial motion for docking in electromechanical coordination. Through the ground experiment, the function of electromagnetic docking device is verified. PubDate: 2022-06-27 DOI: 10.1007/s42423-022-00121-9
Hybrid journal (It can contain Open Access articles)
