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Cpm Neural Network Based Receiver For Leo Satellites, César Benavente, Ángel Martínez, Miguel Muñoz
Cpm Neural Network Based Receiver For Leo Satellites, César Benavente, Ángel Martínez, Miguel Muñoz
Small Satellite Conference
In this paper it is described the development of a receiver for GMSK signals based on the use of neural networks. Two cases are described: one in which the linear approximation of the GMSK signal is employed and other where phase changes are detected. Wide implementation, training and result differences are between both methods and they are described in the paper. The first approach is simpler than the second one, has an easier training but worst results from the point of view of error probability.
Surrey Research On Nitrous Oxide Catalytic Decomposition For Space Applications , Vadim Zakirov, Martin Sweeting, Volker Goeman, Timothy Lawrence
Surrey Research On Nitrous Oxide Catalytic Decomposition For Space Applications , Vadim Zakirov, Martin Sweeting, Volker Goeman, Timothy Lawrence
Small Satellite Conference
Nitrous oxide is introduced as a rocket propellant for small satellites. The reasons for using this propellant on small spacecrafts are discussed. Potential space applications of nitrous oxide are listed. A nitrous oxide catalytic decomposition technique is suggested for restartable spacecraft propulsion. Theoretical performance of a nitrous oxide monopropellant thruster is shown. Basics of nitrous oxide catalytic decomposition are given. Operating principles of a nitrous oxide monopropellant thruster are described. The design of the test apparatus and the set-up for nitrous oxide decomposition are given. Up-to-date achievements of nitrous oxide decomposition research at Surrey are reported. Future design features of …
Development And Transition Of Low-Shock Spacecraft Release Devices For Small Satellites , Andrew Peffer, Eugene Fosness, Capt. Stephen Hill, Waylon Gammill, Dino Sciulli
Development And Transition Of Low-Shock Spacecraft Release Devices For Small Satellites , Andrew Peffer, Eugene Fosness, Capt. Stephen Hill, Waylon Gammill, Dino Sciulli
Small Satellite Conference
Small satellites require a variety of release devices to accomplish mission-related functions such as separation from the launch vehicle, separation from each other, and deployment of instruments. The Air Force Research Laboratory (AFRL) has been working with several private companies to develop low shock, nonpyrotechnic spacecraft release devices to mitigate problems with traditional pyrotechnic release devices. Pyrotechnic devices produce high shock, contamination, and have costly handling requirements due to their hazardous nature. Small satellites are particularly susceptible to shock-related failure because of the close proximity of sensors and instruments to the shock source. In addition, small satellites deployed as constellations …
Designing Command And Telemetry Systems Using Mil-Std-1553 And Ccsds, Ronnie Killough, Michael Mclelland
Designing Command And Telemetry Systems Using Mil-Std-1553 And Ccsds, Ronnie Killough, Michael Mclelland
Small Satellite Conference
The use of the MIL-STD-1553B (1553) communications bus and Consultative Committee for Space Data Systems (CCSDS) standards are becoming increasingly popular in the design of small satellite command and data handling systems. Experience has been gained in the use of these two standards on a number of missions, which could be of benefit to those faced with integrating them into new spacecraft. The 1553 bus presents a number of advantages and disadvantages, both from electrical and data protocol perspectives. The 1553 bus is sometimes specified in the design of systems without considering these issues and without understanding the fundamental characteristics …
Universal Small Payload Interface – An Assessment Of Us Piggyback Launch Capability , Shahed Aziz, Paul Gloyer, Joel Pedlikin, Kimberly Kohlhepp
Universal Small Payload Interface – An Assessment Of Us Piggyback Launch Capability , Shahed Aziz, Paul Gloyer, Joel Pedlikin, Kimberly Kohlhepp
Small Satellite Conference
Small satellites are becoming the solution of choice for planners trying to reduce space mission costs and shorten schedules. Secondary launches are a quick, frequent, low-cost, reliable solution for small satellites. Most international small spacecraft are launched as secondary piggyback payloads, aboard larger more efficient rockets. However, piggyback accommodations in the US are rare, done only on a case-by-case basis, and far from low cost. AeroAstro is presently developing the Universal Small Payload Interface (USPI), a standardized template for integrating and launching small spacecraft. It is designed so that mission developers can design to its requirements in order to be …
Highlights Of Nanosatellite Propulsion Development Program At Nasa-Goddard Space Flight Center , M.S. Rhee, C.M. Zakrzwski, M.A. Thomas
Highlights Of Nanosatellite Propulsion Development Program At Nasa-Goddard Space Flight Center , M.S. Rhee, C.M. Zakrzwski, M.A. Thomas
Small Satellite Conference
Currently the GN&C’s Propulsion Branch of the NASA’s Goddard Space Flight Center (GSFC) is conducting a broad technology development program for propulsion devices that are ideally suited for nanosatellite missions. The goal of our program is to develop nanosatellite propulsion systems that can be flight qualified in a few years and flown in support of nanosatellite missions. The miniature cold gas thruster technology, the first product from the GSFC’s propulsion component technology development program, will be flown on the upcoming ST-5 mission in 2003. The ST-5 mission is designed to validate various nanosatellite technologies in all major subsystem areas. It …
Mems Mega-Pixel Micro-Thruster Arrays For Small Satellite Stationkeeping, Daniel Youngner, Son Thai Lu, Edgar Choueiri, Jamie Neidert, Robert Black Iii, Kenneth Graham, Dave Fahey, Rodney Lucus, Xiaoyang Zhu
Mems Mega-Pixel Micro-Thruster Arrays For Small Satellite Stationkeeping, Daniel Youngner, Son Thai Lu, Edgar Choueiri, Jamie Neidert, Robert Black Iii, Kenneth Graham, Dave Fahey, Rodney Lucus, Xiaoyang Zhu
Small Satellite Conference
Small satellites flying in clusters require periodic “stationkeeping” to keep them in place. The required impulse is very small – the goal is not to keep the individual satellites in rigid formation, but only to keep them in well-defined orbitals with respect to one another. The necessary impulse, therefore, is only the amount needed to overcome the difference in drag between the most-affected and the least-affected satellites in the cluster. Estimates are that the differential drag can be overcome by providing ~1 mNsec (micro-Newton second) to ~1 mN sec (milli-Newton second) every 10 to 100 seconds throughout each satellite’s mission. …
Prototype Development Of A Solid Propellant Rocket Motor And An Electronic Safing And Arming Device For Nanosatellite (Nanosat) Missions, W.L. Boughers, C.E. Carr, R.A. Rauscher, W.J. Slade
Prototype Development Of A Solid Propellant Rocket Motor And An Electronic Safing And Arming Device For Nanosatellite (Nanosat) Missions, W.L. Boughers, C.E. Carr, R.A. Rauscher, W.J. Slade
Small Satellite Conference
Recently, there has been an increased interest in using nanosatellites in space science missions due to many unique science mission architectures that are only possible with a nanosatellite constellation. Hundreds of small and lightweight nanosatellites can form an intelligent constellation acting as a distributed network of instruments. In this way, measurements can be obtained that are not possible with traditional single spacecraft architectures. Such a constellation could take simultaneous, in situ measurements of dynamic phenomena in the Earth’s magnetosphere. This type of data is considered to be a critical element in the NASA Sun-Earth Connection (SEC) roadmap. Currently, the SEC …
Interactive Mission Design Web Site , John Leon, William Cutlip, Mark Hametz
Interactive Mission Design Web Site , John Leon, William Cutlip, Mark Hametz
Small Satellite Conference
The Access To Space (ATS) Group at NASA’s Goddard Space Flight Center (GSFC) supports the science and technology community by facilitating frequent and affordable opportunities for access to space. The ATS Group has developed an interactive Mission Design web site that provides both the information and the tools necessary to assist mission planners in selecting and planning their ride to space. The ATS web site was developed through core partnerships with other government agencies seeking similar tools for their mission planners. Key design features of the site include a searchable mission database and launch vehicle toolboxes. The mission database contains …
Autonomous Control System For Precise Orbit Maintenance, Manop Aorpimai, Yoshi Hashida, Phil Palmer
Autonomous Control System For Precise Orbit Maintenance, Manop Aorpimai, Yoshi Hashida, Phil Palmer
Small Satellite Conference
In this paper, we describe a closed-loop autonomous control system that enables orbit operations to be performed without the need of any ground segment. The growing availability of GPS receivers on satellites provides an excellent means for autonomous orbit determination and our work builds upon previous work on orbit determination algorithms developed here at Surrey. The orbit is described using a set of epicycle parameters which provide an analytic model of LEO orbits. The parameters in this model are estimated onboard the satellite using a Kalman filter. We describe an enhancement to this software which provides both control as well …
Autonomous Operations Experiments For The Distributed Emerald Nanosatellite Mission , Christopher Kitts, Michael Swartwout
Autonomous Operations Experiments For The Distributed Emerald Nanosatellite Mission , Christopher Kitts, Michael Swartwout
Small Satellite Conference
Distributed space systems are often cited as a means of enabling vast performance increases ranging from enhanced mission capabilities to increased system flexibility. Achieving this vision, however, will require radical advances in the automated control of these multi-satellite systems. To explore this challenge, Santa Clara University and Stanford University have initiated development of a simple, low cost, two-satellite mission known as Emerald. The Emerald mission includes several experiments involving the autonomous operation of distributed space systems. First, “low-level” inter-satellite navigation techniques will be explored. Second, “high-level” multi-satellite health and command management functions will be demonstrated. Due to operational considerations and …
Infrastructure For Internet-Based Operations, James Cutler, Gregory Hutchins, Christopher Kitts, Robert Twiggs
Infrastructure For Internet-Based Operations, James Cutler, Gregory Hutchins, Christopher Kitts, Robert Twiggs
Small Satellite Conference
Global access to remote systems is becoming a reality through advances in the Internet. Applied to spacecraft operations, this provides the opportunity for spacecraft operators to access remote system resources from any location with Internet access. As part of its space operations research, Stanford University's Space Systems Development Laboratory (SSDL) is exploring the ability of Internet based operations to improve the cost effectiveness of space mission operation. It is developing a ground station control system to provide computer assisted console control, remote operation, and software agent-based autonomous control. Known as Mercury, the system has been implemented on SSDL's OSCAR-class amateur …
Status Of Chips: A Nasa University Explorer Astronomy Mission, Will Marchant, Ellen Riddle Taylor
Status Of Chips: A Nasa University Explorer Astronomy Mission, Will Marchant, Ellen Riddle Taylor
Small Satellite Conference
In the age of "Faster, Better, Cheaper", NASA's Goddard Space Flight Center has been looking for a way to implement university based world class science missions for significantly less money. The University Explorer (UNEX) program is the result. UNEX missions are designed for rapid turnaround with fixed budgets in the $10 million US dollar range. The CHIPS project was selected in 1998. The CHIPS mission has passed the Concept Study and will be having the Confirmation Review in August 2000. Many lessons have already been learned from the CHIPS UNEX project. This paper will discuss the early issues surrounding the …
Cubesat: A New Generation Of Picosatellite For Education And Industry Low-Cost Space Experimentation , Hank Heidt, Jordi Puig-Suari, Augustus Moore, Shinichi Nakasuka, Robert Twiggs
Cubesat: A New Generation Of Picosatellite For Education And Industry Low-Cost Space Experimentation , Hank Heidt, Jordi Puig-Suari, Augustus Moore, Shinichi Nakasuka, Robert Twiggs
Small Satellite Conference
The launch and deployment of picosatellites from the Stanford University OPAL microsatellite in February 2000 demonstrate the feasibility and practicability of a new age of space experimentation. Two of the six picosatellites deployed from OPAL were built by The Aerospace Corporation in El Segundo, CA and demonstrated new space testing of MEMS RF switches and intersatellite and ground communication with low power wireless radios. These picosatellites weighting less than one kilogram with dimensions of 4x3x1 inch were built as test platforms for DARPA and were constructed and delivered for flight in less than nine months. From this experience, a new …
The Jawsat Mission: Final Report And Lessons Learned , J. Smith, D. Richards, M. Wood, G. Sharp, W. Clapp
The Jawsat Mission: Final Report And Lessons Learned , J. Smith, D. Richards, M. Wood, G. Sharp, W. Clapp
Small Satellite Conference
One Stop Satellite Solutions and the Center for Aerospace Technology recently completed the JAWSAT mission. This was the first flight of the Minotaur launch vehicle and the first time eleven separate micro and pico satellites were placed into orbit with one launch. The JAWSAT project required both new technical designs as well as new programmatic ways of conducting a space mission. Main stream, large satellite, methods were not adequate. Technical lessons learned on this project range from new techniques in versatile, low-cost, structural design to a reasonable method of qualifying commercial off-theshelf electronic components. New methods of final integration and …
Internet Access To Spacecraft, James Rash, Ron Parise, Keith Hogie, Ed Criscuolo, Jim Langston, Chris Jackson, Harold Price
Internet Access To Spacecraft, James Rash, Ron Parise, Keith Hogie, Ed Criscuolo, Jim Langston, Chris Jackson, Harold Price
Small Satellite Conference
The Operating Missions as Nodes on the Internet (OMNI) project at NASA's Goddard Space flight Center (GSFC), is demonstrating the use of standard Internet protocols for spacecraft communication systems. This year, demonstrations of Internet access to a flying spacecraft have been performed with the UoSAT-12 spacecraft owned and operated by Surrey Satellite Technology Ltd. (SSTL). Previously, demonstrations were performed using a ground satellite simulator and NASA's Tracking and Data Relay Satellite System (TDRSS). These activities are part of NASA's Space Operations Management Office (SOMO) Technology Program. The work is focused on defining the communication architecture for future NASA missions to …
Asusat1: Low-Cost, Student-Designed Nanosatellite, Assi Friedman, Brian Underhill, Shea Ferring, Christian Lenz, Joel Rademacher, Helen Reed
Asusat1: Low-Cost, Student-Designed Nanosatellite, Assi Friedman, Brian Underhill, Shea Ferring, Christian Lenz, Joel Rademacher, Helen Reed
Small Satellite Conference
On January 27, 2000 (UTC) ASUSat1 was launched into space onboard Orbital Sciences’ Minotaur rocket. The launch was the culmination of six years of effort by over 400 students. ASUSat1 is an innovative nanosatellite bringing new concepts for low-power, low-mass, highly constrained designs. Its primary mission was earth imaging, with several secondary missions including orbit determination, amateur-radio communications, passive stabilization techniques, attitude detection, and composite-material research. Following the successful launch and deployment of ASUSat1, the satellite operated for 14 hours. In spite of this, the team collected useful data from the satellite, and verified many of the design concepts incorporated …
Recovery Of The Wide-Field Infrared Explorer Spacecraft, David Everett, Thomas Correll, Scott Schick, Kimberly Brown
Recovery Of The Wide-Field Infrared Explorer Spacecraft, David Everett, Thomas Correll, Scott Schick, Kimberly Brown
Small Satellite Conference
The Wide Field Infrared Explorer was developed to perform astronomy using a cryogenically cooled infrared telescope. Shortly after launch, rapid venting of the cryogen, caused by an untimely cover removal, sent the spacecraft into an uncontrollable spin which exceeded 60 revolutions per minute. Over the next week, the WIRE team developed a plan and successfully executed the procedures necessary to de-spin the spacecraft and gain attitude control, but the cryogen for cooling the instrument was depleted. The recovery of the spacecraft enabled a thorough checkout of most of the subsystems, including the validation of several new technologies. Although the primary …
An Attitude Control System And Commissioning Results Of The Snap-1 Nanosatellite , W.H. Steyn, Y. Hashida, V. Lappas
An Attitude Control System And Commissioning Results Of The Snap-1 Nanosatellite , W.H. Steyn, Y. Hashida, V. Lappas
Small Satellite Conference
SNAP-1 is a low-cost nanosatellite build by Surrey Satellite Technology Ltd. (SSTL), it is amongst other objectives a technology demonstrator for 3-axis stabilisation and orbit control for a future constellation of small satellites during formation flying. The satellite uses a single miniature Ymomentum wheel, 3-axis magnetorquer rods and a single butane gas thruster to ensure a nominal nadirpointing attitude with full pitch control and in-track delta-V manoeuvrability. The magnetorquer rods do momentum maintenance and nutation damping of the Y-wheel. The primary attitude sensor used, is a miniature 3-axis fluxgate magnetometer. Precise orbital knowledge will be obtained using a small single …
Systematic Design Of Attitude Control Systems For A Satellite In A Circular Orbit With Guaranteed Performance And Stability , Richard Hull, Chan Ham, Roger Johnson
Systematic Design Of Attitude Control Systems For A Satellite In A Circular Orbit With Guaranteed Performance And Stability , Richard Hull, Chan Ham, Roger Johnson
Small Satellite Conference
In this paper two nonlinear control techniques are developed and compared for the satellite attitude control problem. The first technique is a robust recursive nonlinear method using Euler angle formulation. This method is related to integrator backstepping as well as feedback linearization techniques. However, in this paper a different formulation is presented which overcomes some of the previous difficulties in applying backstepping to this problem by treating the three axis satellite system as a fully coupled set of second order systems. The technique produces a robustly stable controller, which meets desired performance, accounts for system nonlinear behavior, and is easily …
Modular Attitude Control System For Microsatellites With Stringent Pointing Requirements, Simon Grocott
Modular Attitude Control System For Microsatellites With Stringent Pointing Requirements, Simon Grocott
Small Satellite Conference
Advancing technology has allowed for the development of low cost attitude control hardware for microsatellites. However, the attitude control design and software development remain a significant cost driver. The Dynacon High Performance Attitude Control system is a modular control system that makes use of reusable algorithm modules enabling the attitude control system to be applied to several different spacecraft missions with very different performance requirements. The High Performance Attitude Control system is described in this paper, and simulation results are shown for a variety of spacecraft.
Real-Time Attitude And Orbit Control System Of A Small Leo Satellite With Parallel-Processing Approach In A Ground Station, Roger Johnson, Sanjay Jayaram, Lei Sun, Chan Ho Ham
Real-Time Attitude And Orbit Control System Of A Small Leo Satellite With Parallel-Processing Approach In A Ground Station, Roger Johnson, Sanjay Jayaram, Lei Sun, Chan Ho Ham
Small Satellite Conference
A Real-time Attitude and Orbit Control System (AOCS) using a parallel processing approach will be implemented using a Satellite Ground Control Station (SGCS). With this approach, the satellite will collect platform (attitude reference) and payload measurements (at 1Hz) over several orbits and down-link to the SGCS (at 5 KHz) where the real-time filtering, fault detection, diagnosis and corrective (if needed) control is generated. The control commands are up-linked to the satellite before losing telemetry lock. A substantial reduction in on-board computation can provide a cheaper and a higher reliable AOCS. In the proposed scheme, an advanced real-time estimation and control …
Aeroastro’S X-Band Transponder – Meeting The Communication Needs Of Tomorrow’S Small Spacecraft , Eric Aamot, Ray Zenick, Kimberly Kohlhepp
Aeroastro’S X-Band Transponder – Meeting The Communication Needs Of Tomorrow’S Small Spacecraft , Eric Aamot, Ray Zenick, Kimberly Kohlhepp
Small Satellite Conference
This paper will discuss a number of technologies and design philosophies leveraged from commercial industry that AeroAstro has applied to the development of a new spacecraft communications subsystem. Although there has been a recent push toward reducing spacecraft mass and cost, there is no commercially available communications equipment that will significantly contribute to that reduction. While spacecraft mass has dropped more than an order of magnitude in the past ten years, radios have not followed this trend. AeroAstro is developing a highly integrated, power-efficient, low operating voltage X-Band telemetry transponder for small satellite applications. This design leverages emerging technology from …
Effects Of A Distributed Computing Architecture On The Emerald Nanosatellite Development Process , Julie Townsend, Bryan Palmintier, Eric Allison
Effects Of A Distributed Computing Architecture On The Emerald Nanosatellite Development Process , Julie Townsend, Bryan Palmintier, Eric Allison
Small Satellite Conference
Building satellites with greater capabilities on shorter timelines requires changes in development approach. Relative to previous satellite projects in Stanford’s Space Systems Development Laboratory (SSDL), the Emerald Nanosatellite system is highly complex. Its mission requires numerous experiments and relatively sophisticated subsystem capabilities. To develop this system on a short two-year timeline required a new development approach to simplify system integration. As a result, the Emerald development team adopted a modular distributed computing architecture. While this decision imposed many changes on Emerald’s design process, the benefits of the distributed architecture for system integration and testing justified its selection. This approach has …
The Kyushu/Us Experimental Satellite Tether (Quest) Mission, A Small Satellite To Test And Validate Spacecraft Tether Deployment And Operations, Johan Carlson, Yosuke Nakamura
The Kyushu/Us Experimental Satellite Tether (Quest) Mission, A Small Satellite To Test And Validate Spacecraft Tether Deployment And Operations, Johan Carlson, Yosuke Nakamura
Small Satellite Conference
In recent years, an increased effort to design, build, and operate small satellites has taken place in universities and laboratories all over the world. These microsatellites provide numerous flight opportunities for science experiments at a fraction of the cost of larger traditional missions. In addition, there has been an increasing trend towards international cooperation on space projects. From the International Space Station to joint commercial ventures, the future of space progress will be shared by countries around the world. Tomorrow’s engineers must prepare for this challenge. This paper provides an overview of the Kyushu/US Experimental Satellite Tether (QUEST) mission, a …
The Design And Feasibility Study Of Nanosatellite Structures For Current And Future Fsi Micromissions , Badrinarayan Shirgur, Derek Shannon
The Design And Feasibility Study Of Nanosatellite Structures For Current And Future Fsi Micromissions , Badrinarayan Shirgur, Derek Shannon
Small Satellite Conference
To support focused science and engineering micromissions, spacecraft bus designs should minimize mass and maximize design flexibility without reducing capability. This requires a highly efficient spacecraft structure to maintain the required stiffness with a minimal mass. In the following presentation, two design approaches are evaluated for the structure of the Florida Space Institute’s nanosatellite bus. One design uses sandwich construction exclusively, representing the current level of spacecraft structures. The other design uses a cast aluminum primary structure, which is a new approach for nanosats. Based on the evaluation of these two structures, the cast aluminum design is selected for FSI’s …
Opal: Smaller, Simpler, And Just Plain Luckier, James Cutler, Greg Hutchins
Opal: Smaller, Simpler, And Just Plain Luckier, James Cutler, Greg Hutchins
Small Satellite Conference
On January 26, 2000 at 7:03PM PST, Stanford University’s first student built satellite, OPAL – the Orbiting Picosatellite Automated Launcher, roared into space on a modified Minuteman II missile. Students from the Space Systems Development Laboratory spent four years designing, fabricating, and testing the OPAL satellite in preparation for the launch. OPAL’s primary mission objectives were to explore a new mothership/daughtership mission architecture for distributed sensing, to characterize an off-the-shelf magnetometer, and to characterize a suite of off-the-shelf accelerometers. Six DARPA sponsored daughterships, also known as picosatellites, were deployed from OPAL. They were built by The Aerospace Corporation, Santa Clara …
Command And Data Handling Subsystem Design For The Ionospheric Observation Nanosatellite Formation (Ion-F) , John Jensen
Command And Data Handling Subsystem Design For The Ionospheric Observation Nanosatellite Formation (Ion-F) , John Jensen
Small Satellite Conference
This paper describes the approach taken by the ION-F student team in designing a common Command and Data Handling (C&DH) subsystem for three different nanosatellites. It outlines the requirements of the satellites and reasons behind the decision to develop a custom board. The design is based upon industrial-grade components and centered on a Hitachi SuperH RISC Processor. The C&DH subsystem contains a 16 MB telemetry buffer, a digital and analog interface subsystem, and a DMA-oriented CMOS camera framebuffer. Students are fabricating these boards with the assistance of Space Dynamics Laboratory at Utah State University. This design will be flown by …
Digital Cmos Cameras For Attitude Determination, David Meller, Prapat Sripruetkiat, Kristin Makovec
Digital Cmos Cameras For Attitude Determination, David Meller, Prapat Sripruetkiat, Kristin Makovec
Small Satellite Conference
The Ionospheric Observation Nanosatellite Formation (ION-F) satellite cluster consists of three individual spacecraft, which are being developed by the University of Washington (UW), Utah State University (USU), and Virginia Polytechnic Institute and State University (VT). The satellites will demonstrate formation flying and distributed satellite capabilities. A novel component of the Attitude Determination System (ADS) for each satellite is use of low-power, low-mass, inexpensive CMOS cameras for Sun and Earth horizon sensing. This paper describes a candidate camera set of specifications, the configuration of cameras on each ION-F satellite and a sensor fusion scheme for the ADS. Several algorithms for nadir …
Gps Micro Navigation And Communication System For Clusters Of Micro And Nanosatellites , Ray Zenick, Kimberly Kohlhepp
Gps Micro Navigation And Communication System For Clusters Of Micro And Nanosatellites , Ray Zenick, Kimberly Kohlhepp
Small Satellite Conference
Formation flying will quickly revolutionize the way science, remote sensing and surveillance missions are performed in space, enabling a whole new range of applications for small satellites. Currently, there are numerous missions in the planning stages involving formation flying of a constellation of micro or nanosatellites. However, to truly achieve the goals of these formation-flying missions, an accurate means of relative ranging, determining time and position measurements, inter-satellite communications, and controlling the formation states is becoming critical. Today, while there are very expensive products available for positioning and attitude determination, none of them are capable of meeting the precise positioning …