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Advancing The Utility Of Small Satellites With The Development Of A Hybrid Electric-Laser Propulsion (Help) System , Rachel Leach, Thomas Adams, Gerald Murphy
Advancing The Utility Of Small Satellites With The Development Of A Hybrid Electric-Laser Propulsion (Help) System , Rachel Leach, Thomas Adams, Gerald Murphy
Small Satellite Conference
Some of the major space operational capabilities desired for modernizing and transforming our existing space infrastructure include: 1) in-space robotic assembly of modular structures, 2) routine spacecraft repositioning and rescue services, 3) use of formations of satellites that can perform functions not possible with traditional single large structures. All of these applications can make use of a new generation of highly capable micro-satellites. Advantages inherent with the use of small satellite formations include: - enhanced launch flexibility; on-orbit adaptability and reconfigurability; multi-mission capability; and mission longevity. These characteristics equate to greater responsiveness and increased performance requirements at lower costs. Specific …
A Mems Based Experimental Colloid Thruster Package For Nano Satellites, Barry Kent, John Stark, Bob Stevens, Matt Alexander, Adam Baker, Dave Gibbon, Douglas Liddle
A Mems Based Experimental Colloid Thruster Package For Nano Satellites, Barry Kent, John Stark, Bob Stevens, Matt Alexander, Adam Baker, Dave Gibbon, Douglas Liddle
Small Satellite Conference
Colloid propulsion can provide flexible electric propulsion systems capable of delivering both high thrust density and high specific impulse at low power demand. It thus has wide applicability over a range of missions; from end of life de-orbit devices to sophisticated formation flying or disturbance compensation systems. Because of the low system demands colloid propulsion is particularly applicable to small satellites. Scalable micro-fabricated colloid thrusters allow many options: The total thrust available is simply a function of the number of nozzles and, for a given propellant the specific impulse is a function of the acceleration potential. We outline a nano-satellite …
Small Satellite Mars Missions Using Electric Propulsion, Me Price, Ns Wells, Aj Ball, Jc Zarnecki, Fw Taylor
Small Satellite Mars Missions Using Electric Propulsion, Me Price, Ns Wells, Aj Ball, Jc Zarnecki, Fw Taylor
Small Satellite Conference
Two small satellite concepts are presented for low cost Mars system exploration. Both concepts use solar electric propulsion (SEP) to move from a low velocity Earth escape orbit to captured Mars orbits, and so are able to make use of smaller launcher vehicles, while still providing significant payload accommodation, despite their small size. Both missions achieve their Mars system operational orbits in less than 20 months from launch. The Mars Global Atmosphere Survey (MGAS) mission design has a launch mass of 120kg. It uses a QinetiQ T5 ion engine, with around 24kg of Xe propellant, which provides sufficient ÄV for …
Space Exploration Via Technology Demonstration And Small Satellite Missions Flown On Reusable Launch Vehicles, Debra Facktorlepore
Space Exploration Via Technology Demonstration And Small Satellite Missions Flown On Reusable Launch Vehicles, Debra Facktorlepore
Small Satellite Conference
In January 2004, President Bush announced his new vision for Space Exploration, calling for a step-by-step approach to opening new frontiers, furthering scientific research, returning to the Moon, and ultimately enabling exploration to Mars and other destinations. Considering the ultimate objective in exploring the universe and beyond, what are the tools needed to further this vision? A few key components come to mind: affordable and frequent access to space, technology demonstration platforms, and low cost small satellite and robotic missions. Reusable launch vehicles (RLVs), such as Kistler Aerospace’s K-1, and demonstration missions for technology experiments and small satellites together can …
The Geo Quick Ride (Gqr) Program – Providing Inexpensive And Frequent Access To Space , Robert Caffrey, John Baniszewski
The Geo Quick Ride (Gqr) Program – Providing Inexpensive And Frequent Access To Space , Robert Caffrey, John Baniszewski
Small Satellite Conference
This paper examines the feasibility of piggybacking NASA, university, and industry payloads on commercial geosynchronous satellites. In 1998, NASA’s RSDO Office awarded Geo Quick Ride (GQR) study contracts to spacecraft manufacturers to examine the issues concerning the flying of secondary payloads. The study results were very promising. Commercial communications satellites have frequent flights and significant unused resources that could be used to fly secondary payloads. However, manifesting secondary payloads on a commercial revenue generating satellite is a complex problem to solve. The solution requires multiple simultaneous approaches in order to be successful. There are business, economic, technical, schedule, and organizational …
Low Cost Spacelift To Leo, Gto, And Beyond Using The Osp-2 Peacekeeper Space Launch Vehicle, Scott Schoneman, Lou Amorosi, Ron Willey, Dan Cheke
Low Cost Spacelift To Leo, Gto, And Beyond Using The Osp-2 Peacekeeper Space Launch Vehicle, Scott Schoneman, Lou Amorosi, Ron Willey, Dan Cheke
Small Satellite Conference
The Peacekeeper (PK) Space Launch Vehicle (SLV) is a new launch vehicle for providing cost effective spacelift for small-to-medium, Government-sponsored spacecraft, including addressing an emerging need of small Geosynchronous (GEO) spacecraft. This vehicle is being developed by Orbital Sciences under the Orbital Suborbital Program 2 (OSP-2) contract with the United States Air Force (USAF) Space and Missile Systems Center (SMC) Detachment 12 Rocket System Launch Program (RSLP). Preliminary designs and capabilities were presented at the 2003 Small Satellite Conference. In the year since, there has been significant interest in the PK SLV, and the first missions have been initiated with …
Micro Labsat - Technology Demonstration Microsatellite For Future Missions, Toru Yamamoto, Hidekazu Hashimoto, Shinichiro Nishida, Shinichi Kimura, Shinichi Nakasuka
Micro Labsat - Technology Demonstration Microsatellite For Future Missions, Toru Yamamoto, Hidekazu Hashimoto, Shinichiro Nishida, Shinichi Kimura, Shinichi Nakasuka
Small Satellite Conference
Micro LabSat is a technology demonstration microsatellite. The important concept is "easy to use". Microsatellites are relatively simple and low-cost, so users can carry out technology demonstration experiments without too much cost and risk. The experiments focusing on on-orbit servicing technologies were planned. The satellite was launched on December 14, 2002 by an H-IIA launch vehicle. All pre-planned experiments were successfully accomplished. Micro LabSat provided many researchers an opportunity to perform several experiments on-orbit, and indicated the merit of microsatellites as a future technology demonstrator.
Using Nanosats As A Proof Of Concept For Space Science Missions: Quakesat As An Operational Example , Scott Flagg, Tom Bleier, Clarke Dunson, John Doering, Louis Demartini, Paul Clarke, Lew Franklin, Jeannie Seelbach, Janine Flagg, Mary Klenk, Victor Safradin, Jamie Cutler, Allen Lorenz, Eric Tapio
Using Nanosats As A Proof Of Concept For Space Science Missions: Quakesat As An Operational Example , Scott Flagg, Tom Bleier, Clarke Dunson, John Doering, Louis Demartini, Paul Clarke, Lew Franklin, Jeannie Seelbach, Janine Flagg, Mary Klenk, Victor Safradin, Jamie Cutler, Allen Lorenz, Eric Tapio
Small Satellite Conference
Several previous satellites (Cosmos 1809 and Aureol-3) had detected anomalous extremely low frequency (ELF) magnetic field signals prior to and after large earthquakes around the early 90's. There were questions regarding signal levels, signal structure, frequency ranges, timing, and the ambient noise environment that made it difficult to specify larger science satellites to thoroughly test the theory that ELF might be a precursor signal to large earthquakes. An inexpensive nanosat (QuakeSat) was built, launched in June 2003, and flown to help determine the design parameters and values needed to build a research satellite for this mission.
Bilsat-1: First Year In Orbit- Operations And Lessons Learned, Gökhan Yüksel, Önder Belce, Hakan Urhan, Luis Gomes, Andy Bradford, Neville Bean, Alex Da Silva Curiel
Bilsat-1: First Year In Orbit- Operations And Lessons Learned, Gökhan Yüksel, Önder Belce, Hakan Urhan, Luis Gomes, Andy Bradford, Neville Bean, Alex Da Silva Curiel
Small Satellite Conference
BILSAT-1 is an enhanced micro satellite designed and manufactured in the framework of a KHTT programme between SSTL (UK) and TUBITAK-BILTEN (Turkey). The satellite was launched by a COSMOS 3M launch vehicle from the Plesetsk Cosmodrome in Russia on September 27, 2003. After being injected in a sun synchronous orbit at a 686 km altitude, it was commissioned successfully via ground control station at TUBITAK-BILTEN. After commissioning, the operations have started. Many images have been taken over Turkey and over various locations around the world. In contrast to large national Earth Observation satellites such as LANDSAT, EO-1 and Terra, BILSAT …
Commissioning Of A Small Satellite Constellation - Methods And Lessons Learned , Dave Gibbon, Lee Boland, Neville Bean, Yoshi Hashida, Alex Da Silva Curiel, Martin Sweeting, Phil Palmer
Commissioning Of A Small Satellite Constellation - Methods And Lessons Learned , Dave Gibbon, Lee Boland, Neville Bean, Yoshi Hashida, Alex Da Silva Curiel, Martin Sweeting, Phil Palmer
Small Satellite Conference
The Disaster Monitoring Constellation consists of a series of four spacecraft built by Surrey Satellite Technology Ltd. The aim of the constellation is to be able to perform daily revisits over any point on the Earth such that 32m resolution images can be taken. These images can be used for daily monitoring of natural and man-made disasters. The constellation is made up of four spacecraft. Alsat-1, is an 88 kg microsatellite, which was launched on 28th Nov 2002, for the Algerian national space agency CNTS. It was joined in orbit by three additional microsatellites on 27th September 2003, Nisat-1 (Nigerian …
The Most Microsatellite Mission: One Year In Orbit , Simon Grocott, Robert Zee, Jaymie Matthews
The Most Microsatellite Mission: One Year In Orbit , Simon Grocott, Robert Zee, Jaymie Matthews
Small Satellite Conference
The MOST (Microvariability and Oscillations of Stars) microsatellite, launched from the Plesetsk Cosmodrome in Russia on June 30, 2003, has had a very successful first year in orbit. MOST is an astronomical science mission designed to measure brightness variations as small as a few parts per million in bright nearby stars. This application demands a pointing accuracy that is not normally associated with microsatellites. One requirement for the MOST mission was that the spacecraft point the boresight of the science instrument (a 15-cm optical telescope feeding a CCD camera/photometer) to an accuracy of 25 arcseconds. In practice, the MOST attitude …
The Iris Project: A New Architecture Or A Small Satellite Imaging Mission, Quinn Young, Todd Mosher, Jared Clements, Pranay Gupta, Matt Warner
The Iris Project: A New Architecture Or A Small Satellite Imaging Mission, Quinn Young, Todd Mosher, Jared Clements, Pranay Gupta, Matt Warner
Small Satellite Conference
Utah State University students have developed an earth-imaging satellite mission designed for specifically for the promising, low-cost RASCAL launch platform. Designed over a semester-long space system design class, the mission is intended to capture high quality images of earth from a low-Earth orbit. The total mission cost is estimated at $10 million including satellite design, fabrication, launch, and mission operations. Students used the university’s new Space System Analysis Laboratory, a concurrent design center, to assess design trades and develop the system architecture. The mission architecture, mission elements and satellite design are presented.
A Highly Modular Scientific Nanosatellite: Test, David Voss, A. Kirchoff, D.P. Hagerman, D.C.H Tan, J.J. Zapf, Jeff Dailey, Art White, H.D. Voss, M. Maple, Farzad Kamalabadi
A Highly Modular Scientific Nanosatellite: Test, David Voss, A. Kirchoff, D.P. Hagerman, D.C.H Tan, J.J. Zapf, Jeff Dailey, Art White, H.D. Voss, M. Maple, Farzad Kamalabadi
Small Satellite Conference
A powerfully instrumented, reliable, low-cost 3-axis stabilized nanosatellite is in final design using novel technologies. The Thunderstorm Effects in Space: Technology (TEST) nanosatellite implements a new, highly modular satellite bus structure and common electrical interface that is conducive to satellite modeling, development, testing, and integration flow. TEST is a low-cost ($0.1 – 0.2 M) nanosatellite (30kg) in final development by Taylor University and the University of Illinois through the Air Force Office of Space Research (AFOSR) University Nanosatellite program. TEST implements a strong variety of plasma, energetic particle, and remote sensing instrumentation with the objective of understanding how lighting and …
Science Mission Scenarios Using “Palmsat” Picosatellite Technologies, Craig Underwood, Vaios Lappas, Alex Da Silva Curiel, Martin Unwin, Adam Baker, Martin Sweeting
Science Mission Scenarios Using “Palmsat” Picosatellite Technologies, Craig Underwood, Vaios Lappas, Alex Da Silva Curiel, Martin Unwin, Adam Baker, Martin Sweeting
Small Satellite Conference
The Recent efforts to provide low cost access to space for education and technology demonstration have led to the concept of the pico-satellite – a satellite of the order of 1 kg in mass. Students at the Surrey Space Centre, are developing such a satellite – PalmSat – which has a number of potential scientific applications when launched in a swarm, or alongside a micro-satellite “mother-craft”. PalmSat builds upon the success of Surrey’s 6.5 kg SNAP-1 nano-satellite, launched in 2000, and yet takes the concept of spacecraft miniaturization a step further, from a modular commercial-off-the-shelf (COTS) technology based spacecraft formed …
An Approach To Automated Health Monitoring & Control For Space Systems , Roger Johnson, Sanjay Jayaram, Dan Hand, Jami Ward
An Approach To Automated Health Monitoring & Control For Space Systems , Roger Johnson, Sanjay Jayaram, Dan Hand, Jami Ward
Small Satellite Conference
Modern satellites require a great degree of human attention to insure functionality. In this paper we discuss UCF’s micro-satellite program aimed at designing automated satellite control systems with fault recovery and health monitoring capabilities designed to ease the operation of satellites. Three major topics are discussed: the organization of UCF’s micro-satellite effort, work on health monitoring & autonomous control and finally work conducted on a satellite simulator.
Low-Cost Ground Station Antenna Arrays For Microspacecraft Mission Support, James Wells, Mark Sdao, Robert Zee
Low-Cost Ground Station Antenna Arrays For Microspacecraft Mission Support, James Wells, Mark Sdao, Robert Zee
Small Satellite Conference
Employing microspacecraft on interplanetary missions entails meeting numerous unresolved technical challenges. One such problem is how to maintain a reliable communications link with the microspacecraft over long distances. When considering the feasibility and costs of several alternatives, it has been shown that a ground station array is an ideal solution to the problem. Simulations and experiments performed at the Space Flight Laboratory of the University of Toronto Institute for Aerospace Studies have demonstrated that it is possible to create such an array using a group of amateur radio ground stations. When enhanced through the use of several digital signal processing …
Platform For Attitude Control Experiment (Pace): An Experimental Three-Axis Stabilized Cubesat, Jung-Kuo Tu, Shi-Hua Wu, Chen-Chi Chu
Platform For Attitude Control Experiment (Pace): An Experimental Three-Axis Stabilized Cubesat, Jung-Kuo Tu, Shi-Hua Wu, Chen-Chi Chu
Small Satellite Conference
Owing to their low cost, fast development time, and multi-discipline educational purpose, CubeSats have been widely advocated by universities in recent years. However, few have employed three-axis stabilization schemes due mainly to the limitation of power and mass. The PACE, Platform for Attitude Control Experiment for short, is a three-axis stabilizing CubeSat developed at the National Cheng Kung University. It is a 20x10x10 cm3 double cube satellite weight less than 2-kg. A miniature momentum wheel is employed to achieve stability alone the pitch (orbit normal) axis. Magnetic coils are used to generate control torques to stabilize roll and yaw axes. …
Structure Design For Modular Platform And Capability On The Ususat 2 Micro-Satellite , Joël Quincieu
Structure Design For Modular Platform And Capability On The Ususat 2 Micro-Satellite , Joël Quincieu
Small Satellite Conference
In the last fifteen years, small satellites have opened a window through which the aerospace industry can rapidly access low earth orbit at a fraction of the cost required by large spacecrafts. Due to its extensive experience with the Space Dynamics Laboratory (SDL), Utah State University (USU) has given students the opportunity to experience the design of such small satellites, nanosatellites or micro-satellites in technical terms. Through the University Nanosat programs organized mainly by the Air Force Research Laboratory (AFRL), USU students have now been involved in two satellite designs since 1999. The author has been and is contributing to …
An Electrically Actuated Pin-Puller For Space Application Using Nickel- Titanium Memory Alloy, Peter Cipollo, Brendan Surrusco
An Electrically Actuated Pin-Puller For Space Application Using Nickel- Titanium Memory Alloy, Peter Cipollo, Brendan Surrusco
Small Satellite Conference
The Local Ionospheric Measurements Satellite (LionSat) is an ionospheric investigation nanosatellite that is being developed by an interdisciplinary team of students at The Pennsylvania State University. As part of its primary science mission, the satellite will be used to examine the plasma environment surrounding it via a set of plasma probes. These probes extend linearly on booms from the midsection of the satellite and must remain in a stowed, locked position during launch. This paper discusses the design and fabrication of an electrically actuated pin-puller used to secure the booms in the spacecraft that makes use of Nickel–Titanium (NiTi) memory …
Preliminary Design Of A Very-Low-Thrust Geostationary Transfer Orbit To Sun-Synchronous Orbit Small Satellite Transfer, Chris Rampersad
Preliminary Design Of A Very-Low-Thrust Geostationary Transfer Orbit To Sun-Synchronous Orbit Small Satellite Transfer, Chris Rampersad
Small Satellite Conference
Small satellites have proven their viability for conducting meaningful missions at a fraction of the cost of larger satellites. Correspondingly, the demand for small satellite missions is increasing as is the need for more sophisticated low-cost satellites. To enable these more advanced missions, this paper analyzes the feasibility of using a low-thrust propulsion system to transfer to a mission orbit from a readily available launch opportunity. Speci¯cally, a geosynchronous transfer orbit (GTO) launch to a sun-synchronous orbit (SSO) small satellite trajectory is examined. The transfer from GTO to SSO orbit is designed using a direct optimization method. Due to the …
Space Technology 5: Enabiling Future Micro-Sat Constellation Science Missions, Candace Carlisle, Evan Webb, James Slavin
Space Technology 5: Enabiling Future Micro-Sat Constellation Science Missions, Candace Carlisle, Evan Webb, James Slavin
Small Satellite Conference
The Space Technology 5 (ST-5) Project is a part of NASA’s New Millennium Program. ST-5 will consist of a constellation of three micro satellites, each approximately 25 kg in mass. The mission goals are to demonstrate the research-quality science capability of the ST-5 spacecraft; to operate the three spacecraft as a constellation; and to design, develop and flight-validate three capable micro-satellites with new technologies. ST-5 is designed to measurably raise the utility of small satellites by providing high functionality in a low mass, low power and low volume package. The whole of ST-5 is greater than the sum of its …
Cassiope: A Canadian Smallsat-Based Space Science And Advanced Satcom Demonstration Mission , Gregory Giffin, Waqar-Un-Nissa Ressl, Andrew Yau, Peter King
Cassiope: A Canadian Smallsat-Based Space Science And Advanced Satcom Demonstration Mission , Gregory Giffin, Waqar-Un-Nissa Ressl, Andrew Yau, Peter King
Small Satellite Conference
Cassiope, which stands for ‘CASCADE Smallsat and Ionospheric Polar Explorer’, is a recently announced and challenging smallsat mission. Primed by MacDonald Dettwiler (MDA), and enabled by contributions from the Canadian Space Agency (CSA) and Technology Partnerships Canada (TPC), Cassiope will support two distinct payloads and objectives. A general mission overview followed by a focus on the technical and scientific aspects of both payloads is presented. The first payload is a suite of space science instruments that in sum are referred to as e-POP, the Enhanced Polar Outflow Probe. Developed by a scientific team led by the University of Calgary, e-POP …
Earthshine – A Deep Space Science Mission Using Small Satellite Technology, Nigel Morris, Mike Lockwood, Mark Smith, Roger Sides
Earthshine – A Deep Space Science Mission Using Small Satellite Technology, Nigel Morris, Mike Lockwood, Mark Smith, Roger Sides
Small Satellite Conference
The EARTH-Sun-Heliosphere INteractions Experiment is a novel space mission designed to answer key questions about how Earth’s climate and space environment are influenced by the Sun. Using a small satellite orbiting about the L1 Lagrange point located approximately 1.5 million kilometres from the Earth, the scientific payload will have a unique and continuous view of the dayside of Earth, and an uninterrupted view of the Sun. From here measurements of the reflective properties of clouds over large viewing angles will be made, whilst simultaneously monitoring the variations and effects of the electromagnetic, particle and field outputs of the Sun. The …
A Solar Kite Mission To Study The Earth's Magneto-Tail, V. Lappas, B. Wie, C. Mcinnes, L. Tarabini, L. Gomes, K. Wallace
A Solar Kite Mission To Study The Earth's Magneto-Tail, V. Lappas, B. Wie, C. Mcinnes, L. Tarabini, L. Gomes, K. Wallace
Small Satellite Conference
Solar sails have been studied in the past as an alternative means of propulsion for spacecraft. Recent advances in solar sail technology and the miniaturisation of technology can drive these systems much smaller (< 5 kg mass, < 10 m sail diameter) than existing sails, while still having a high delta-V and acceleration capability. With these unique capabilities of miniature solar sails, called solar kites, some very unique space science missions can be achieved which are difficult to be implemented using conventional propulsion techniques. One such unique candidate mission is to study the Earth's magneto-tail. The paper lays out the main design features and technologies of a solar kite mission/platform and demonstrates that a cluster of solar kites with science payloads can provide multiple, in-situ measurements of the dynamic evolution of energetic particle distributions of the rotating geomagnetic tail of Earth. With a unique design, a solar kite proves to be an efficient, affordable and versatile solution for the mission analysed with a significant science return.
Living With A Star (Lws) Space Environment Testbeds (Set) Mission Carrier Overview And Capabilities, Robert Patschke, Janet Barth, Ken Label, Carolyn Mariano, Karen Pham, Dana Brewer, Michael Cuviello, David Kobe, Carl Wu, Donald Jarosz, Nicholas Teti, Scott Appelbaum, Katie Barthelme
Living With A Star (Lws) Space Environment Testbeds (Set) Mission Carrier Overview And Capabilities, Robert Patschke, Janet Barth, Ken Label, Carolyn Mariano, Karen Pham, Dana Brewer, Michael Cuviello, David Kobe, Carl Wu, Donald Jarosz, Nicholas Teti, Scott Appelbaum, Katie Barthelme
Small Satellite Conference
NASA has initiated the Living With a Star (LWS) Program to develop the scientific understanding to address the aspects of the Connected Sun-Earth system that affect life and society. A goal of the program is to bridge the gap between science, engineering, and user application communities. This will enable future science, operational, and commercial objectives in space and atmospheric environments by improving engineering approaches to the accommodation and/or mitigation of the effects of solar variability on technological systems. The three program elements of the LWS Program are Science Missions; Targeted Research and Technology; and Space Environment Testbeds (SETs). SET is …
Minimizing Mission Risks Through Emulating Space Communications Architectures, Rich Slywczak, Frances Lawas-Grodek, Diepchi Tran, Thong Luu, Allen Holtz, Brenda Ellis
Minimizing Mission Risks Through Emulating Space Communications Architectures, Rich Slywczak, Frances Lawas-Grodek, Diepchi Tran, Thong Luu, Allen Holtz, Brenda Ellis
Small Satellite Conference
The goal of launching breakthrough missions with a minimal amount of risk at a reasonable cost is achievable regardless whether the mission is large, such as NASA’s International Space Station, or small, such as CHIPSat. To meet these goals, satellite missions must rely on new tools that detect any liabilities to the project during pre-launch testing. NASA/Glenn Research Center (GRC) is currently developing an emulation testbed to assist missions with validating requirements and resolving issues, whether science or communication, before moving to an operational status. The Space Communications Emulation Facility (SCEF) will serve as a nationally accessible NASA facility. In …
A Novel Approach To A High Speed, Large Memory Spacecraft Data Storage Unit, Louis Piché, Blair Gordon, Kjell Magnussen, Len Laba
A Novel Approach To A High Speed, Large Memory Spacecraft Data Storage Unit, Louis Piché, Blair Gordon, Kjell Magnussen, Len Laba
Small Satellite Conference
A high capacity Data Storage Unit is key to the store and forward mode of operation for numerous science and commercial missions and services that generate very high data volumes at high data rates. This paper introduces just such a commercial service in the form of the CASCADE service. In order for this service to succeed, one of the key spacecraft components is the Data Storage Unit, or DSU. Besides high capacity, the Data Storage Unit needs to have a relatively random access, low power consumption, and a reasonable size and mass. There are currently two storage technologies that appear …
Miniature Space Gps Receiver By Means Of Automobile-Navigation Technology, Yusuke Hamada, Nobuyuki Tomita, Hirobumi Saito, Takahide Mizuno, Kousuke Kawahara, Kenji Shinkai, Hiroyuki Sasaki
Miniature Space Gps Receiver By Means Of Automobile-Navigation Technology, Yusuke Hamada, Nobuyuki Tomita, Hirobumi Saito, Takahide Mizuno, Kousuke Kawahara, Kenji Shinkai, Hiroyuki Sasaki
Small Satellite Conference
Miniature space GPS receivers have been developed by means of automobile-navigation technology. The weight and power consumption of the GPS receiver are 35 g and 1 W, respectively. We expanded the frequency sweep range in order to cover large Doppler shift in orbit. We tested the performance in low earth orbits by means of a GPS simulator. The GPS receiver succeeded in cold start acquisition in less than 60 minutes. The GPS receiver for automobile- navigation generates position data with time tag which is not accurate enough to space application. The GPS receiver was modified to output pseudorange data with …
The Use Of Small Cell Lithium-Ion Batteries For Small Satellite Applications, Chris Pearson, Carl Thwaite, Nick Russel
The Use Of Small Cell Lithium-Ion Batteries For Small Satellite Applications, Chris Pearson, Carl Thwaite, Nick Russel
Small Satellite Conference
During solar eclipse, spacecraft rely on batteries to power all on-board electrical systems. Advances in battery technology have lead to lighter products that, in turn, allow spacecraft to fly heavier and more capable payloads. AEA Technology has pioneered the current state of the art in the space community1: Lithium-ion battery technology. Traditionally space batteries were composed of a single series connected string of cells. The cells are sized (in terms of capacity) according to mission requirements and so cell qualification programmes for individual missions are common. The small cell approach involves taking Commercially available Off The Shelf (COTS) Lithium-ion cells, …
Arc-Minute Nanosatellite Attitude Control: Enabling Technology For The Brite Stellar Photometry Mission, Kieran Carroll, Slavek Rucinski, Robert Zee
Arc-Minute Nanosatellite Attitude Control: Enabling Technology For The Brite Stellar Photometry Mission, Kieran Carroll, Slavek Rucinski, Robert Zee
Small Satellite Conference
The BRIght-star Target Explorer (BRITE) mission plans to make photometric observations of some of the brightest stars in the sky, which are also among the intrinsically most luminous stars, in order to examine these stars for variability with a precision at least 10 times better than that achievable using ground-based observations. Because of the brightness of the target stars, a very small (3cm) aperture telescope collecting light for a camera equipped with a CMOS detector will suffice. The small aperture size and low power consumption of the CMOS detector are compatible with nanosatellite size and power constraints, and so BRITE …