Development of On-board Computer Module for Formation Flying and Cluster Operation Nano-satellites
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본 연구에서는 초소형 위성을 이용한 위성 편대 및 군집 운용 시 실시간으로 위성 간의 상대 위치 정보를 제공할 수 있는 통합 항법용 모듈형 온보드 컴퓨터(On-board Computer, OBC)를 개발하였다. 모듈은 구조적으로는 큐브위성의 기준 규격에 맞게 설계하되 사용자가 원하는 무선 통신 모듈 및 항법용 Global Positioning System(GPS) 장비를 적용할 수 있도록 확장성을 고려하였다. 개발된 OBC는 제품 개발 및 제작 이후 야외 테스트를 통해 저전력 Micro Controller Unit(MCU)로 군집 운용을 수행하는 초소형 위성들의 통합 항법 및 실시간 데이터 동기화 요구 처리속도를 만족함을 확인하였다. 또한, 열진공, 방사능 시험을 거쳐 우주급 환경에서 정상 작동함을 확인하였으며, 진동시험의 경우 underfill 공정을 추가하면 정상적으로 요구조건을 만족할 수 있음을 확인하였다. 이를 통해 향후 수요가 늘어날 군집 운용을 위한 위성군 개발의 핵심 부품인 OBC의 대량 생산 체계를 구축하였다.Keywords:
CubeSat
On board
View Video Presentation: https://doi.org/10.2514/6.2021-1704.vid In the past decade CubeSats have made their way into the spotlight. They have evolved from small university educational opportunities to industry and governments using them make new discoveries and monetize space. However, with the small, constrained CubeSat form factor there is often a need to expand the CubeSat through deployable mechanisms once the satellite is in space. This paper is a survey of deployable structures and their actuating mechanisms for CubeSats. The goal of this paper is to provide the applications within which deployable structures have been used in the past for CubeSats, the mechanisms with regards to how they deploy, the lessons learned, and limitations of the various types of deployables. The inputs to this paper come from a relational database in development to track launched CubeSat missions with deployable structures. From this database we can find insightful trends. This paper specifically focuses on the first decade of CubeSat deployables, from 2000 to 2010.
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The increase in space exploration missions in recent years gave way to the development of a volume-efficient and cost-effective nanosatellite like the cube satellite (CubeSat) which can be developed and fabricated in a relatively short time. With its size and design, CubeSat parts like casings can be produced and assembled through 3D printing to produce inexpensive satellites. Research in this area is undeniably important to maximize the rapid development of CubeSats. While progress has been made, challenges remain in applying 3D printing technology in the development of CubeSats. In this paper, the current status regarding the advancement of 3D printing for CubeSat applications is discussed. First, important issues about the common materials for CubeSat and potentially 3D printing materials for CubeSats are addressed. Second, 3D printing CubeSat parts through the feasible structure design models by combining material and parameter designs are explored from a wide range of references. And also, 3D printing of cube satellite parts by DOST AMCen and STAMINA4Space has also been demonstrated. Lastly, an outlook on the future direction of the 3D printed CubeSat for the Philippines space program is provided.Keywords: Cube satellite, CubeSat, 3D printing, high-performance polymers
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To meet the challenge of improving CubeSat access to space, a team of graduate students at the Naval Postgraduate School (NPS) is developing the NPS CubeSat Launcher (NPSCuL). NPSCuL is an enabling technology that seeks to utilize excess capacity on US launch vehicles to provide CubeSat developers with routine, high capacity, low-cost access to space. The launcher currently integrates eight Cal Poly Poly-Picosatellite Orbital Deployers (P-PODs) with a deployment sequencer in a simple structure. NPSCuL will be able to accommodate up to twenty four units of CubeSat volume on a single launch using only one ESPA-class payload interface. This capability has the potential to advance US space technology and ensure that the next generation of US space professionals will remain on the cutting edge of very small satellite development. A flight-qualified NPSCuL is expected to be complete in late 2009 with a potential launch as early as August of 2010. NPSCuL provides “coach-class-to-orbit:” a high-capacity, lowcost way to deliver CubeSats to space that is consistent with US launch capability, the CubeSat specification, the needs of the growing CubeSat community, and US national interests.
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Inflatable
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Nihon University is developing micro satellite "CubeSat" proposed by USSS and we aim at the launch in 2003. Participating in this project means that we can earn the basic know how of developing a satellite and buildup a foundation to do a simple experiment in space. We suggest the mission of our "CubeSat" as attitude estimation by measuring temperature using platinum resistance element. In this presentation, we will introduce the subsystem of our CubeSat, current status of the mission analysis, and report the result of the operation experiment in ARLISS.
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Presentation (obstetrics)
Foundation (evidence)
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Since the beginning of the CubeSat program, developers have been pushing the envelope of the capabilities that can be achieved in such a small and standardized package. As CubeSat missions have become more complicated the external surface area of these cubes has become a limiting factor for the missions. In order to harvest as much power as possible, the external surfaces are usually dedicated solely to solar arrays, thus limiting the external surface area that can be used for the primary mission. The ALL-STAR mechanical team has developed an innovative and unique system that allows for both the electrical power subsystem engineer and the science instrument engineer to have full access to the exterior of the satellite without sacrificing any of the quality or capabilities of the CubeSat and its overall mission. In order to accomplish this, the ALL-STAR team has developed mechanisms that deploy both solar arrays and the payload section from the standard 3U CubeSat. The PEZ (Payload Extension Zone) effectively doubles the available area for the solar array on the CubeSat as well as allowing the payload to have access to the exterior of the satellite. These mechanisms are also innovative in that they use simple concepts and mechanisms to greatly reduce their impact on the mass and volume of the CubeSat as a whole. Through this cooperative design between maximum power collection and payload access, the ALL-STAR bus will allow for even greater CubeSat capabilities to be achieved.
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Currently, 10 National Institutes of Technology (KOSEN) are collaborating to develop a 2U CubeSat. This study aims to develop a CubeSat ground model that allows KOSEN students who wish to participate to learn CubeSat. The CubeSat ground model is a standard 10cm×10cm×20cm (2U) CubeSat size. Furthermore, it consists of a similar subsystem as the actual CubeSat, enabling semi-autonomous operation by OBC, charging and feeding by solar cells, and data transmission by wireless devices. Moreover, a structure system with a space where mission equipment can be installed will be designed, so that students can deepen their understanding of the satellite mission. These plans will be used in the model CubeSat production course at the KOSEN Space Camp 2019. This paper describes features of the developed model CubeSat and introduces the model CubeSat production course.
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In this paper, we present high-resolution image and video CubeSat (HiREV), the first constructed 6 U platform to reach the space technology test bed stage, developed by the Korea Aerospace Research Institute (KARI). The CubeSat system is a low-cost platform that has been widely applied to various space missions, from missions involving earth observation to deep space. Despite the emergence of the CubeSat technology worldwide, the CubeSat market in Korea is still in the beginning stages, and a standard testing platform is also in demand. For this reason, KARI is starting to develop a 6 U CubeSat platform, which includes a less than 3 U bus system and greater than 3 U payload space. HiREV has been developed with locally manufactured parts, creating a domestic commercial off-the-shelf infrastructure for CubeSat and 3 m resolution camera payload development. Core flight software has also been applied as an on-board flight software system. Presently, we have developed the main system, while HiREV is under space environmental testing.
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Recently, there has been a large push for university participation in space exploration from organizations such as NASA. But to participate, students and professors must be able to simulate an environment similar to space so they may test the design of their spacecraft. Most university CubeSat programs are targeted toward PhD matters, with some help from undergraduate students. In this paper, we explain a novel approach to design and develop a low-cost platform for testing a CubeSat attitude control system. This platform is developed while keeping a minimal physical footprint within the lab. In addition, all research and development for this testing platform will be performed solely at the undergraduate level. The testing platform was developed with a modest grant from local industries and university support and is being used to perform research on CubeSat attitude determination and controls systems (ADCS). Off the shelf CubeSat ADCS are expensive, but they are a major component of a successful CubeSat design and development. The goal of this paper is to show smaller organizations a way to enter CubeSat research, by offering a low cost, small footprint, frictionless test stand to aid in design and development of CubeSat ADCS [1-3]. The main principle in creating this frictionless test stand will be the physics of an air bearing. By creating a thin cushion of air between the air bearing and the base, a near frictionless environment is achieved [1]. The PI 150mm-diameter hemispherical air bearing was utilized for this, as it has an adequately-sized platform and a load capacity of 160 kg. The air bearing also need a pedestal to be mounted on which was manufactured out of aluminum and then anodized. This pedestal was then bolted to an industrial cart for portability and stability. Then, by utilizing a standard air compressor that can be found at many different hardware stores, the system can be brought online. It is important to note that standard air compressors that are typically used for household purposes are efficient for operation of this system, but can produce undesired noise and vibration. To reduce this, the portable stand was lined with a noise-reducing material. While this adds an extra cost to the test stand, it makes the system quiet and adds extra stability. The completed frictionless test stand offers 360° of freedom on the Z axis and ±45° of freedom on the X and Y axes and has been produced for $7,220. This test stand provides an excellent, low cost, low footprint solution for emulating the frictionless environment of outer space and is ideal for testing rotational motion capabilities of ADCS.
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Environmental tests
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A Cubesat is a miniature sized Satellite having a volume of exactly one liter with a mass of no more than 1.33 kilograms. The design of a Cubesat is simple which allows low cost for its development. This paper describes the outline of a proposed Cubesat Project, named IR_SAT, by the students of Institute of Space Technology. The project aims for design and development of a 10cm cubic satellite weighing less than 1kg. The major mission of Satellite is to study the vegetation pattern and soil moisture on the areas of Pakistan. For this monitoring IR Imager will be used that is unaffected by the Earth Albedo. The satellite is supposed to operate at an altitude of 400 km above Sea and perform the limited LEO science mission. In addition to the IR_Sat description, the detailed subsystems are also discussed along with their corresponding budget in this paper.
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CubeSat Project is an international, educational and practical program, and many universities and companies join in the project. A CubeSat is a pico-satellite sized of 10cm^*10cm^*10cm, less than 1kg in weight, and 18 CubeSats are planned to launch at May 1 of 2002 by a Russian rocket, Dnepr. We, TITech group, are now developing a CubeSat for the launch opprtunity. The objectives of TITech CubeSat Project are design/development of pico satellite equipped with bus components under the leadership of students, and reduce the total costs by using commercial off-the-shelf (COTS) components. In this paper, we explain the design and the development schedule of TITech CubeSat.
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Quasi-Zenith Satellite System
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