1,205 research outputs found
INDEX: A Piggy-Back Satellite for Advanced Technology Demonstration
This paper describes outline of the piggy-back satellite INDEX for demonstration of advanced satellite technologies as well as for a small scale science mission. INDEX satellite will be launched in 2002 by Japanese H2-A. The satellite is mainly controlled by the high-speed, fault-tolerant on-board RIes processor (three-voting system of SH-3). The attitude control is a compact system of three-axis stabilization. Although the size of INDEX is small (50Kg class), several newly-developed technologies are applied to the satellite system, including silicon-on-insulator devices, variable emittance radiator, solar-concentrated paddles, lithium-ion battery, and GPS receiver with all-sky antenna-coverage. These technology developments will be applied to Japanese scientific space exploration in future
Application of advanced technology to space automation
Automated operations in space provide the key to optimized mission design and data acquisition at minimum cost for the future. The results of this study strongly accentuate this statement and should provide further incentive for immediate development of specific automtion technology as defined herein. Essential automation technology requirements were identified for future programs. The study was undertaken to address the future role of automation in the space program, the potential benefits to be derived, and the technology efforts that should be directed toward obtaining these benefits
Naval Postgraduate School NPSAT1 Small Satellite
Paper presented at the ESA Small Satellite Systems and Services SymposiumThe NPSAT1 mission, conceived and developed by
the Naval Postgraduate School (NPS) Space Systems
Academic Group (SSAG), is sponsored and executed
by the DoD Space Test Program (SMC SDD). The
small satellite is manifested for launch aboard the
STP-1 Atlas V Mission due to launch in December
2006. The main objective of the NPSAT1 program is
to provide educational opportunities for the offi cer
students in the Space Systems Curricula at NPS through
the design, testing, integration, and fl ight operations of
a small satellite. The 82 kg (180 lbs) satellite will be
earth-pointing using a novel, low-cost, 3-axis attitude
control scheme. NPSAT1 will provide a platform for a
number of spacecraft technology experiments, including
a lithium-ion battery, a confi gurable, fault-tolerant
processor (CFTP) experiment, and fl ight demonstrations
of commercial, off-the-shelf (COTS) components such
as microelectromechanical systems (MEMS) rate sensors
and a digital camera. The spacecraft command and data
handling (C&DH) subsystem is NPS-designed, featuring
low-power with error-detection-and-correction (EDAC)
memory, an ARM720T microprocessor, and running
Linux as the operating system. Two other experiments are
provided by the Naval Research Laboratory to investigate
ionospheric physics. This paper presents an overview of
the spacecraft, its subsystems, and the challenges of a small satellite program in a university environment.Naval Postgraduate School, Monterey, California
Technology for the Future: In-Space Technology Experiments Program, part 2
The purpose of the Office of Aeronautics and Space Technology (OAST) In-Space Technology Experiments Program In-STEP 1988 Workshop was to identify and prioritize technologies that are critical for future national space programs and require validation in the space environment, and review current NASA (In-Reach) and industry/ university (Out-Reach) experiments. A prioritized list of the critical technology needs was developed for the following eight disciplines: structures; environmental effects; power systems and thermal management; fluid management and propulsion systems; automation and robotics; sensors and information systems; in-space systems; and humans in space. This is part two of two parts and contains the critical technology presentations for the eight theme elements and a summary listing of critical space technology needs for each theme
Autonomous Robots for Active Removal of Orbital Debris
This paper presents a vision guidance and control method for autonomous
robotic capture and stabilization of orbital objects in a time-critical manner.
The method takes into account various operational and physical constraints,
including ensuring a smooth capture, handling line-of-sight (LOS) obstructions
of the target, and staying within the acceleration, force, and torque limits of
the robot. Our approach involves the development of an optimal control
framework for an eye-to-hand visual servoing method, which integrates two
sequential sub-maneuvers: a pre-capturing maneuver and a post-capturing
maneuver, aimed at achieving the shortest possible capture time. Integrating
both control strategies enables a seamless transition between them, allowing
for real-time switching to the appropriate control system. Moreover, both
controllers are adaptively tuned through vision feedback to account for the
unknown dynamics of the target. The integrated estimation and control
architecture also facilitates fault detection and recovery of the visual
feedback in situations where the feedback is temporarily obstructed. The
experimental results demonstrate the successful execution of pre- and
post-capturing operations on a tumbling and drifting target, despite multiple
operational constraints
Analysis of spacecraft anomalies
The anomalies from 316 spacecraft covering the entire U.S. space program were analyzed to determine if there were any experimental or technological programs which could be implemented to remove the anomalies from future space activity. Thirty specific categories of anomalies were found to cover nearly 85 percent of all observed anomalies. Thirteen experiments were defined to deal with 17 of these categories; nine additional experiments were identified to deal with other classes of observed and anticipated anomalies. Preliminary analyses indicate that all 22 experimental programs are both technically feasible and economically viable
Advances in Spacecraft Systems and Orbit Determination
"Advances in Spacecraft Systems and Orbit Determinations", discusses the development of new technologies and the limitations of the present technology, used for interplanetary missions. Various experts have contributed to develop the bridge between present limitations and technology growth to overcome the limitations. Key features of this book inform us about the orbit determination techniques based on a smooth research based on astrophysics. The book also provides a detailed overview on Spacecraft Systems including reliability of low-cost AOCS, sliding mode controlling and a new view on attitude controller design based on sliding mode, with thrusters. It also provides a technological roadmap for HVAC optimization. The book also gives an excellent overview of resolving the difficulties for interplanetary missions with the comparison of present technologies and new advancements. Overall, this will be very much interesting book to explore the roadmap of technological growth in spacecraft systems
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