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The STEP Cube Lab (Cube Laboratory for Space Technology Experimental Projects) is a 1U cube satellite developed by the Space Technology Synthesis Laboratory of Chosun University to be launched in 2015. Its mission objective is twofold: to determine which of the fundamental space technologies researched at domestic universities, will be potential ca...
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... we focus on a CPV system for cube satellite applications that uses a MEMS based lens array system. This system has the potential to increase power generation when the angle between the sunlight and the solar cell is zero by effectively concentrating solar energy on solar panels. *Non-explosive holding and release mehcanism is described in Fig. 1 Recently, cube satellites have been used for increasingly complex missions. Considering their extremely small package size, the range of functions that they can perform gives rise to the use of numerous mechanisms and deployable structures that are necessary for achieving challenging mission-related functions. The cube satellite ...
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... mechanism was designed for high load capacity, negligible shocks, and synchronous release of multi-deployable structures. Figure 1 shows both the stowed and released configurations of the non-explosive separation mechanism. The mechanism consists of a constraint bolt, two segmented nuts, a pin, a nylon cable, and two springs. ...
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... Fig. 1(b). The springs allow the release of the constraint bolt when the segments of the separated nut rotate away from the bolt around the pin at the bottom of the mechanism. The nichrome wire is positioned on the V-shaped interface and is located far away from the mechanism's heat sinks to avoid heat loss and ensure a successful cut. The ...
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... separated nut rotate away from the bolt around the pin at the bottom of the mechanism. The nichrome wire is positioned on the V-shaped interface and is located far away from the mechanism's heat sinks to avoid heat loss and ensure a successful cut. The nichrome wire is also reciprocally woven in a zigzag line through the nylon cable, as shown in Fig. 1(a). This guarantees reliable cutting through the cable by avoiding poor contact between the nichrome burn wire and the cables, which can be caused by a decrease in the cable tension due to partial cutting of the cable. Fig. 2 shows an example of a successful release sequence of the mechanism after triggering the nichrome burn wire at the ...
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Citations
... 13 Moreover, given the geographic characteristics of the Latin American region (e.g. thousands of kilometres of mountains and highlands, and hundreds of volcanoes), 14 satellite telecommunication could better respond to the specific requirements and demands of people facing connectivity precarity due to remoteness from large cities and/or more populated places, or even poverty. Therefore, this satellite-based technology might contribute to tackling the effects of inequality in this respect. ...
... According to information generated by the Ministry of Economy, 17 the Mexican aerospace sector has positioned itself nationally as the fourth 13 Ibid., 64. 14 most relevant after the food industry, the automotive industry and the electricelectronic sector; likewise, it has become an active supplier of levels one and two. Based on the above, this paper aims to analyse possible paths for social sustainability practices in the supply chain of the Mexican space sector. ...
Attracting young people’s interest into science has always been a challenge and something that is rarely achieved. This is mainly due to the misconception that science is all about numbers and calculations, which is obtained by the difficulty presented in their years in school. Although it is true that to understand an exact natural science it is necessary to have a basic knowledge in areas related to physics, mathematics, or chemistry. Many of these subjects are often focused in a non-applicational way and for this reason most students don’t understand in a clear way the main concepts of these subjects. Nowadays, this is slowly changing due to the growing number of schools, associations and universities that are showing more interest in prioritizing the promotion of natural scientific areas of study and investigation. In South America the most common way to promote this interest in natural science and its applications is through science fairs, and contests on different topics (robotics, astronomy, programming, video games, etc.). In the region, the best results were seen in contests, which were initially developed in universities but were later implemented in schools as well. Regarding the space area there are different types of contests, but the one that attracts attention and stands out most is the CanSat Contest that has been implemented more and more throughout different countries in South America. A striking feature of this contest is its slogan “You can build a satellite”. The aim is to involve students in space projects by providing a brief yet complete knowledge about the design and implementation of a space mission. This contest focusses on applied science but also boosts the participants to gain more confidence to achieve greater goals in the space field. The principal objective of the CanSat Contest apart from simulating a real space mission is to involve participants in the design and construction processes of components that make up the different subsystems of a satellite. Like for example the electrical power system, communication system, payload, etc. All these sub-systems must enter in a container in the size of a soda can which will be positioned at an altitude between 300 to 500 m above the surface and have to transmit a signal (wireless, not Wi-Fi) in real-time to a ground station connected to a computer, where the data and results obtained by the satellite are displayed. The CanSat Contest reflected the best-selected option by the company Sur Aerospace and the EMI University to foment science and technology space groups in Bolivia. Groups that were formed by students from different universities were offered the possibility to compete in this type of contest that takes place in many countries around the world and is qualified by the same rules. For this reason, these institutions held the first CanSat contest in Bolivia, in which involved eight participating groups and more than 40 students.
... As a result, these loads will be disregarded in the current work, and will not be mentioned again. Previous works that considered dynamic launch loads included Aborehab et al. [40], Oh et al. [41], Cote et al. [42], Okuyama et al. [43], Park et al. [44], and others. ...
Satellite systems undergo several operational phases during their service life, including the assembly phase, ground transportation phase, the launch phase, and the in-orbit operation phase. Among these phases, the one that imposes the highest level of loadings on the satellite is the launch phase. This phase involves a number of highly dynamic loads, all being imposed upon the satellite simultaneously. Investigation of the responses of the structural subsystem of a satellite to these loadings, namely its maximum deformations and maximum von Mises stresses, is critical if a reasonably high level of confidence is to be achieved. This confidence is in terms of ensuring that no material yielding develops in the structure as a result of the imposed launch loadings. In an earlier work, the structural subsystem of a conceptual microsatellite was designed, employing aluminum 6061 alloy as its material. It was then modified through introducing sets of parametrically defined geometric patterns as perforation patterns to remove material, towards reducing the structure’s total mass, as an alternative to employing composite materials. That effort led to a mass reduction percentage of 23.15%. The current work’s research effort focused on computing the responses of the perforated structure to three of the dynamic launch loads that are imposed upon satellites while being launched, namely quasi-static, random, and shock loads. These responses were then compared to those of the baseline, unperforated, version of the same structure. The values of these loads were taken from the relevant sources, with the values being nominal, and represented the loads that any satellite must qualify for before it can be accepted by the provider for inclusion in a launcher. After imposing these load values upon the structural design it was found that the structural responses indicated that the structure would successfully survive these loads without developing stresses that would lead to material yielding failure. This was deduced from computing the yield margins of safety for each loading case, and all margin values were positive, indicating that the structure, at its current development stage, did have sufficient capacity to withstand these loads without material yielding. This reinforced the conclusion of the earlier work, namely that the perforation concept did have sufficient merit to be further developed towards being implemented in future satellite designs.
... Raviprasad et al. [4] they provided the modal, harmonic and random vibration analysis of the nano-satellite mission and findings were compared with the standard mechanical specifications of the CubeSat and launch vehicle providers. Oh et al. [5] introduced a CubeSat mission structure concept, based on the 1U Model, developed by the Chosun University Space Technology Synthesis Laboratory. Furthermore, the validity of their proposed design was investigated through quasi-static and modal analysis. ...
... Most of the focus is on the vibrations of the system during take-off. In one study a quasi-static load of g = 42.3 was applied to each axis of the CubeSat and the electronic components were also considered with a safety factor of 1.25 [19] . Most of the modal results were shown to be successful, such as the first eigenfrequency of the bending mode for the Polyimide modules of frequency 155 Hz [19] and a first harmonic frequency of a nanosat to be greater than its fundamental frequency [20] . ...
... In one study a quasi-static load of g = 42.3 was applied to each axis of the CubeSat and the electronic components were also considered with a safety factor of 1.25 [19] . Most of the modal results were shown to be successful, such as the first eigenfrequency of the bending mode for the Polyimide modules of frequency 155 Hz [19] and a first harmonic frequency of a nanosat to be greater than its fundamental frequency [20] . ...
The United Arab Emirates (UAE) goal is to be among the top globally recognized countries within the field of cosmology, astronomy, technological innovation and advanced technology to counterpoint human information. Space exploration has been a really necessary goal to the UAE, and the country’s program hit completely different milestones concerning science and exploration. Lately, a huge milestone in the UAE’s burgeoning space industry, led by the Mohammed Bin Rashid Space Centre (MBRSC) was reached when the first UAE national successfully boarded an international space station.
A satellite designed and developed by UAE students was launched on November 17th, 2018. The UAE’s space sector is presently moving fast towards new technologies and explorations reaching to place the name of the UAE among the highest countries in technology and analysis.
Due to the increased interest in the outer space, more research regarding satellites are being conducted over the years. The earliest man-made satellites were larger than some of today’s satellites. Lately, there have been a variety of small satellites (nanosatellites) that have the benefits of their small size, cost, lightweight and easy to launch specifications.
Research has been developed regarding the thermal and structural behavior of nanosatellites (CubeSats). This thesis dives deep into both the thermal and structural analysis to look over the behavior of the Nanosatellite entitled “MYSAT-1” during its mission around the earth (July 1st, 2019 and December 31st, 2019) under several conditions, including different temperatures and positions.
The launch period is considered to be the most critical stage of a CubeSat mission due to the fact that the failure percentage is relatively high, and the chances of survival are slim. Therefore, the structural analysis is very important regarding the success of such missions in which it will help in increasing the chances of success by performing several tests and analysis to test the limitation values for each material used in a CubeSat formation. Additionally, the value of the Factor of Safety (FoS) is measured to assure the safe performance of the material properties during launch.
The verification procedure used in this thesis is divided into two methods: verifying by comparing the results with values obtained from Literature Review and other resources, other values were compared to the experimental result obtained from the lab, the operational temperature ranges of the internal components, and the percentage errors from all verifications were calculated.
The obtained results were then interpreted to formulate recommendations that can be used to enhance the safety, material-used, durability and compatibility of future CubeSat related missions, research, and to increase the level of confidence regarding the success of MYSAT-1 launch process.
... Bürger et al. [9] presented static and modal analyses of the structure subsystem of a CubeSat project developed at the Brazilian Technological Institute of Aeronautics. Oh et al. [10] introduced the structure design of a CubeSat mission, based on the 1U Standard, developed by the Space Technology Synthesis Laboratory of Chosun University. In addition, the validity of their proposed design has been investigated by performing quasi-static and modal analyses. ...
This work presents hands on experience of the configuration process and strength analyses of a student’s CubeSat project at the German University in Cairo. The static and dynamic performance of the primary structure, during launching phase, are investigated and checked against the strength requirements in addition to making sure that stiffness constraints imposed by the P-POD and the candidate launchers are met. The static response of the primary structure is performed using ANSYS Finite Element Software by exposing the structure to the maximum quasi static launch load in each of three flight directions separately. Modal analysis results are presented in order to check the compliance of the longitudinal and lateral natural frequencies, of the proposed model, with the launchers requirements. In addition, random vibration response is performed using frequency domain analysis, assuming that the structure will be subjected to launch random vibration loads in all directions. Finally, fatigue life analysis is presented in order to ensure that primary structure will safely survive the launching mechanical environments.
... Oh, et. al. peformed the structural design and performed modal and quasi-static analysis of a 1U cubesat [2]. Sekerere et. ...
The aim of this study is to design a 3 Unit CubeSat structure performing finite element analysis under static, dynamic and thermal loads. The main idea of this process is to construct a 3U CubeSat main frame that can structurally endure launching process and space environment. To accomplish the task, a 3U CubeSat structure is designed and standard loads that a 3 unit CubeSat structure has to endure are obtained. After the selection of a suitable material, modal analysis, quasi-static launch analysis and thermal stress analysis coupled with heat transfer analysis are accomplished in Abaqus environment. Finally, the results are evaluatedand endurance level of the design is determined.
... For example, Jung et al. [12] evaluated the mechanical reliability of a remote drive unit under random launch vibration based on Steinberg's theory. In addition, this theory was used for investigating the mechanical reliability of electronic PCBs for cube satellite applications [13] and electronics for military applications [14]. However, Steinberg's theory has theoretical limitations which cause errors in mechanical safety prediction results. ...
The fatigue damage that accumulates on a solder joint under a launch vibration environment is a major cause of failure in spaceborne electronics. Thus, predicting the mechanical safety of the solder joint in the structural design phase is important to guarantee a successful space mission. This paper proposes a mechanical design methodology to predict and ensure more reliable mechanical safety of the solder joints of a plastic ball grid array (PBGA) and a thin-shrink small outline package (TSSOP) under launch random vibration excitation. Random vibration fatigue tests for a sample printed circuit board (PCB) assembly were performed to assess the fatigue life of BGA and TSSOP solder joints. The effectiveness of the proposed structural design methodologies was evaluated by comparing the margin of safety calculated from various analysis approaches and the random vibration fatigue test results of the PCB specimen.
... The results of FEA were compared with theoretical predictions. Quasi-static and vibration analysis of 1U cubesat were presented by (Hyun et al, 2014). (SHEPENKOV, 2013) studied the effects of deployable tape spring boom on the structure of the satellite. ...
... In order to estimate Von Misses stress, equivalent elastic strain and total deformation, the static analysis on satellite structure was applied. In this analysis 200 N load was applied in the centroid of all sides of the CubeSat structure while the design load of launching was (51 g) which can be calculated from following equation (Hyun et al, 2014) the qualification level of was depends on the mass of CubeSat (Robert C. Baumann, 1996). The design load was acted in the lower surface of structure. ...
The current work focuses on vibration and modal analysis of KufaSat structure
using ANSYS 16 program. Three types of Aluminum alloys (5052-H32, 6061-T6 and 7075-
T6) were selected for investigation of the structure under design loads. Finite element
analysis (FEA) in design static load of 51 g was performed. The natural frequencies for five
modes were estimated using modal analysis. In order to ensure that KufaSat could withstand
with various conditions during launch, the Margin of safety was calculated. The results of
deformation and Von Mises stress for linear buckling analysis were also performed. The
comparison of data was done to select the optimum material for KufaSat structures.
... In this study, to achieve a reliable electrical contact between the MEMS thrusters and its control board in launch withstanding any kind of test mentioned above [10] . The MEMS sensor are used in flights and developed and in the history of 12 successive PSLV flights. ...
The use of Micro Electrical and Mechanical Systems (MEMS) in the field of electrical and mechanical based domains is becoming the brains of micro devices day by day. This paper represents about the recent trends that MEMS concept has been profoundly used. MEMS sensors technology has been used in the various domains such as engineering, medical & space equipment, telecommunication RF systems, bio technology etc..,By this paper we have shown some of the technologies already existed in each domain which will give the immense cutting edge enhancements, improvements in research and shows the need of MEMS concept in the field of research. The development of MEMS technology will be integrating the mechanical and electrical systems into the single base which will be the building blocks for the overall equipment.
... STEP Cube Lab (Cube Laboratory for Space Technology Experimental Project) is the first pico-class satellite being developed at the SSTL (Space Technology Synthesis Laboratory) of Chosun University, and is scheduled to be launched in the beginning of 2017 [6]. The main objective of its mission is to perform on-orbit verification of results from space-related research conducted at domestic universities. ...
... Its primary objective is to perform in-orbit verification of candidate fundamental space technologies for future space missions. The payloads [6] to be verified in the STEP mission are a variable emittance radiator, a PCM (Phase Change Material), a MEMS-based solid propellant thruster 5) , a concentrating photovoltaic (CPV) power system, and a novel non-explosive holding and release mechanism triggered by nichrome burn wire heating. The function and performance of these technologies have been previously verified by laboratory-level research at universities [5], but their design effectiveness has never been qualified in outer space or on-ground simulated space environments. ...
A MEMS solid propellant thruster array shall be operated within an allowable range of operating temperatures to avoid ignition failure by incomplete combustion due to a time delay in ignition. The structural safety of the MEMS thruster array under severe on-orbit thermal conditions can also be guaranteed by a suitable thermal control. In this study, we propose a thermal control strategy to perform on-orbit verification of a MEMS thruster module, which is expected to be the primary payload of the STEP Cube Lab mission. The strategy involves, the use of micro-igniters as heaters and temperature sensors for active thermal control because an additional heater cannot be implemented in the current design. In addition, we made efforts to reduce the launch loads transmitted to the MEMS thruster module at the system level structural design. The effectiveness of the proposed thermo-mechanical design strategy has been demonstrated by numerical analysis.
