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Small Satellite Conference — Mon, 13 Aug 2012 12:15:00 PDT

Due to file size, the papers and presentations have been organized by technical session. For the complete 2012 technical program, download all documents in "Additional Files" on this page.

EDSN: A Large Swarm of Advanced Yet Very Affordable, COTS-based NanoSats that Enable Multipoint Physics and Open Source Apps

Jim Cockrell et al. — Mon, 13 Aug 2012 16:00:00 PDT

The NASA Office of the Chief Technologist’s (OCT) Small Spacecraft Technology Program (SSPT) has sponsored a 24-month, $11M project called Edison Demonstration of SmallSat Networks (EDSN). The goals of EDSN are to demonstrate a swarm of small, inexpensive satellites with novel on-orbit communications capabilities, and to demonstrate their suitability as a future platform for distributed Space Weather or other scientific measurements that require distributed, multipoint, time-synchronized measurements in low Earth orbit (LEO). EDSN will demonstrate the unique capabilities that a swarm of nanosatellites has to offer, both as a platform for distributed science data acquisition, and as a means of cost and risk reduction by virtue of being a functionally distributed system-of-systems. EDSN will demonstrate advanced communications, including cross-satellite ad-hoc data communications network, for extremely flexible data correlation and distribution, simplified operations, and efficient downlink of swarm data. EDSN will support a science instrument payload capable of measuring “space weather” data that, when combined with data taken from other members of the satellite swarm, can yield spatially and temporality correlated data maps impossible to acquire from a single satellite. Finally, EDSN will investigate the utility of commercial, off-the-shelf electronics (such as consumer grade smart phone for avionics) for use as capable, yet very inexpensive satellite components. The EDSN technologies will be validated during a planned 60-day operations period.

Experiences in Combining Cubesat Hardware and Commercial Components from Different Manufacturers in Order to Build the Nano Satellite AISat/Clavis-1

Falk Nohka et al. — Thu, 16 Aug 2012 12:05:00 PDT

The off-the-shelf availability of a large variety of Cubesat components from different manufacturers enables building-block-like configuration of Cubesat systems. Is it possible to utilize these components to build a nano satellite for scientific payloads? The German Aerospace Center (DLR) internal engineering group Clavis, with the goal of developing a flexible, modular nano satellite platform, was confronted with implementing their design into the AISat mission. The challenges, solutions and lessons learned is what this paper shall transport. From the early steps in designing a satellite bus for DLR internal small payloads to adapting this concept to a real payload and implementing a lot of experience was gained with respect to cost of modularity, interdependency of commercially available components from different manufacturers, verification, and integration. The initial Clavis concept was intended to be flexible with respect to the payload it may support, to be modular in order to provide for different mission scenarios, and to mainly consist of standardized components which enable a mission life time of up to one year (and possibly beyond). With the adoption of the AISat payload the conceptual design had to be adapted to the specific requirements of the payload since it was already defined.

DISC Experiment Overview and On-Orbit Performance Results

Andrew Nicholas et al. — Thu, 16 Aug 2012 12:00:00 PDT

The Digital Imaging Star Camera (DISC) experiment has successfully imaged star fields from the International Space Station (ISS). DISC is a Naval Research Laboratory (NRL) led payload developed jointly by NRL and the Utah State University Space Dynamics Laboratory (SDL) to advance miniaturized technology for accurate precision pointing knowledge in space which is a critical mission requirement for many scientific and operational payloads. The low size, weight and power (<10x10x10 >cm, <1kg, <1 W) sensing platform that will provide an enhanced pointing capability for nano- and pico- satellite busses. It is flying on the ISS as part of the Air Force Space Test Program STP-H3 flight to provide a proof of concept for DISC experiment. This technology represents a key transition from large, high cost, long-timescale programs to small, low-cost, rapid response science enabling sensing platforms. This paper will focus on the instrument design and on-orbit mission performance.

Commissioning of the NigeriaSat-2 High Resolution Imaging Mission

Alex da Silva Curiel et al. — Thu, 16 Aug 2012 11:45:00 PDT

The manufacture of the NigeriaSat-2 spacecraft was completed in 2010, and was successfully launched in August 2011. This is a state-of-the-art small satellite Earth observation mission including several innovations not previously seen on small spacecraft, which will provide high duty cycle imaging of the Earth in high resolution. It will be used by the Nigerian government for mapping and to monitor a number of environmental issues within the country. The key requirements of this mission are to provide high volume mapping data, coupled with highly accurate image targeting and geolocation, and sufficient agility to enable a wide range of complex operational modes. This paper focuses on the challenges associated with designing a spacecraft system that can meet these requirements on a satellite with a mass of less than 270kg. The paper will describe how the stereo, mosaic and other imaging modes can be employed using the agility of the spacecraft. Inertia calibration and on-board navigation techniques used to give the required targeting accuracy are discussed, and the interaction between the attitude control system and the mechanical design is detailed. The payload isolation system used to ensure image quality and geolocation performance is also described. An overview of the final test and launch campaign, and first in-orbit results from the satellite commissioning are provided.

Initial Flight Results of the RAX-2 Satellite

John Springmann et al. — Thu, 16 Aug 2012 11:30:00 PDT

The second Radio Aurora Explorer satellite, RAX-2, is a triple CubeSat studying the formation of plasma irregularities in Earth’s ionosphere. The spacecraft was developed jointly by SRI International and the University of Michigan, and it is the first satellite funded by the National Science Foundation. RAX-2 launched October 28, 2011 and is currently operating on orbit. RAX uses a bistatic radar configuration to study the ionospheric irregularities: a ground-based incoherent scatter radar station illuminates the irregularities, and the RAX-based radar receiver measures radar scatter from the irregularities. RAX has successfully measured radar scatter from the ionospheric irregularities, providing unprecedented auroral region measurements. In this paper, we review the mission goals and satellite development, and discuss initial flight results from the mission. This includes a summary of results from the first detection of radar scatter, power system performance, spacecraft attitude dynamics, global UHF noise measurements, and data download strategies and results of partnering with the amateur radio community.

QbX - The CubeSat Experiment

Stephen Arnold et al. — Thu, 16 Aug 2012 11:15:00 PDT

The Naval Research Laboratory (NRL) launched 2 QbX CubeSats from Cape Canaveral Air Force Station on December 8, 2010 as secondary payloads aboard SpaceX’s Falcon 9 launch vehicle, leveraging the flight opportunity provided by the first COTS Demo Flight of SpaceX’s Dragon Module. This paper will describe the development of the QbX CubeSats, present measured flight data, and evaluate the overall mission performance of the QbX CubeSats.

Operationally Responsive Space-1 (ORS-1) Lessons Learned

Thomas Davis et al. — Thu, 16 Aug 2012 11:00:00 PDT

Operationally Responsive Space-1 (ORS-1) is the first ORS Office operational satellite and an important milestone to demonstrate the capability to meet emerging and persistent warfighter needs in operationally relevant timelines. Launched in June 2011, ORS-1 was initiated at the direction of the Commander, U.S. Strategic Command and the DoD Executive Agent for Space to address a U.S. Central Command (USCENTCOM) need for enhanced battlefield awareness. The ORS Office led an assessment that produced a unique solution with proven operational utility providing timely coverage and responsive theater tasking that avoided the burden of traditional top-down procurements and provides future growth leveraging upgrades in airborne/space assets. The ORS-1 team went from the drawing board to the launch pad within 32 months and earned early combatant command acceptance in September 2011, less than 90 days after liftoff. ORS-1 is the first and only dedicated space intelligence capability for USCENTCOM, introducing Operationally Responsive Space as a new paradigm for DoD. The $224M program includes the satellite based on Goodrich's SYERS-2 payload and the proven ATK TacSat-3 bus, two mission data downlink sites, mission data processing system, and satellite command and control ground system, interfaces with the existing airborne ISR exploitation and dissemination systems, Minotaur I launch vehicle, and operations. The team doggedly adhered to a “good enough to win” approach to deliver a capability that was affordable, rapid, and risk tolerant. ORS-1 provides USCENTCOM an assured ISR capability that cannot be preempted by support to other users. It is an enabler for sustaining operations and objectives in a highly volatile region and is laying the path for future rapid reaction space systems. This paper will review the program objectives and accomplishments to date as well as the Lessons Learned already being applied to other responsive space initiatives.

First Results From the GPS Compact Total Electron Content Sensor (CTECS) on the PSSCT-2 Nanosat

Rebecca Bishop et al. — Thu, 16 Aug 2012 10:45:00 PDT

The Compact Total Electron Content Sensor (CTECS) is a GPS radio occultation instrument designed for picosatellite and nanosatellite platforms that utilizes a COTS receiver, modified receiver firmware, and a custom designed antenna. CTECS was placed on the Pico Satellite Solar Cell Testbed-2 (PSSCT-2) nanosatellite that was installed on the Space Shuttle Atlantis (STS-135 mission). PSSCT-2 was successfully released from the shuttle on 20 July 2011 and reentered on 8 December 2011. After approximately four weeks of spacecraft checkout and attitude adjustments, CTECS was powered on and began its mission to obtain ionospheric measurements of the total electron content (TEC) and scintillation (S4). CTECS obtained 13.5 hours of measurements over the mission lifetime. We will show the first successful relative TEC and electron density profiles obtained from a GPS sensor on a nanosatellite. We present the capabilities of the sensor, the challenges encountered during development and operation, and the subsequent mitigations employed.

DICE Mission Design, Development, and Implementation: Success and Challenges

Chad Fish et al. — Thu, 16 Aug 2012 10:30:00 PDT

Funded by the NSF CubeSat and NASA ELaNa programs, the Dynamic Ionosphere CubeSat Experiment (DICE) mission consists of two 1.5U CubeSats which were launched into an eccentric low Earth orbit on October 28, 2011. Each identical spacecraft carries two Langmuir probes to measure ionospheric in-situ plasma densities, electric field probes to measure in-situ DC and AC electric fields, and a magnetometer to measure in-situ DC and AC magnetic fields. Given the tight integration of these multiple sensors with the CubeSat platforms, each of the DICE spacecraft is effectively a “sensor-sat” capable of comprehensive ionospheric diagnostics. Over time, the sensor-sats will separate relative to each other due to differences in the ejection velocity and enable accurate identification of geospace storm-time features, such as the geomagnetic Storm Enhanced Density (SED) bulge and plume. The use of two identical sensor-sats permits the de-convolution of spatial and temporal ambiguities in the observations of the ionosphere from a moving platform. In addition to demonstrating nanosat constellation science, the DICE mission downlink communications system is operating at 3 Mbit/s. To our knowledge, this transmission rate is a factor of 100 or more greater than previous CubeSat missions to date. This paper will focus on the DICE mission design, implementation, and on-orbit operations successes as well as the challenges faced in implementing a high-return science mission with limited resources. Specifically, it will focus on the lessons learned in integrating, calibrating, and managing a small constellation of sensor-sats for global science measurements.