Randall Rose

The CYGNSS nanosatellite constellation hurricane mission

The Cyclone Global Navigation Satellite System (CYGNSS) is a spaceborne mission concept focused on tropical cyclone (TC) inner core process studies. CYGNSS attempts to resolve the principle deficiencies with current TC intensity forecasts, which lies in inadequate observations and modeling of the inner core. CYGNSS consists of 8 GPS bistatic radar receivers deployed on separate nanosatellites. The primary science driver is rapid sampling of ocean surface winds in the inner core of tropical cyclones.

New Ocean Winds Satellite Mission to Probe Hurricanes and Tropical Convection

AbstractThe Cyclone Global Navigation Satellite System (CYGNSS) is a new NASA earth science mission scheduled to be launched in 2016 that focuses on tropical cyclones (TCs) and tropical convection. The mission’s two primary objectives are the measurement of ocean surface wind speed with sufficient temporal resolution to resolve short-time-scale processes such as the rapid intensification phase of TC development and the ability of the surface measurements to penetrate through the extremely high precipitation rates typically encountered in the TC inner core. The mission’s goal is to support significant improvements in our ability to forecast TC track, intensity, and storm surge through better observations and, ultimately, better understanding of inner-core processes. CYGNSS meets its temporal sampling objective by deploying a constellation of eight satellites. Its ability to see through heavy precipitation is enabled by its operation as a bistatic radar using low-frequency GPS signals. The mission will depl...

Avionics of the Cyclone Global Navigation Satellite System (CYGNSS) microsat constellation

The Cyclone Global Navigation Satellite System (CYGNSS), which was recently selected as the Earth Venture-2 investigation by NASAs Earth Science System Pathfinder (ESSP) Program, measures the ocean surface wind field with unprecedented temporal resolution and spatial coverage, under all precipitating conditions, and over the full dynamic range of wind speeds experienced in a tropical cyclone (TC). The CYGNSS flight segment consists of 8 microsatellite-class observatories, which represent SwRIs first spacecraft bus design, installed on a Deployment Module for launch. They are identical in design but provide their own individual contribution to the CYGNSS science data set. Subsystems include the Attitude Determination and Control System (ADCS), the Communication and Data Subsystem (CDS), the Electrical Power Supply (EPS), and the Structure, Mechanisms, and Thermal Subsystem (SMT). This paper will present an overview of the mission and the avionics, including the ADCS, CDS, and EPS, in detail. Specifically, we will detail how off-the-shelf components can be utilized to do ADCS and will highlight how SwRIs existing avionics solutions will be adapted to meet the requirements and cost constraints of microsat applications. Avionics electronics provided by SwRI include a command and data handling computer, a transceiver radio, a low voltage power supply (LVPS), and a peak power tracker (PPT).

CYGNSS: NASA Earth Venture Tropical Cyclone Mission

The NASA Earth Venture Cyclone Global Navigation Satellite System (CYGNSS) is a spaceborne mission scheduled to launch in October 2016 that is focused on tropical cyclone (TC) inner core process studies. CYGNSS attempts to resolve one of the principle deficiencies with current TC intensity forecasts, which lies in inadequate observations and modeling of the inner core. CYGNSS is specifically designed to address these two limitations by combining the all-weather performance of GNSS bistatic ocean surface scatterometry with the sampling properties of a constellation of satellites. CYGNSS measurements of bistatic radar cross section of the ocean can be directly related to the near surface wind speed, in a manner roughly analogous to that of conventional ocean wind scatterometers. The technique has been demonstrated previously from space by the UK-DMC mission in 2005-6.

Stabilized dispersive focal plane systems for space

As the costs of space missions continue to rise, the demand for compact, low mass, low-cost technologies that maintain high reliability and facilitate high performance is increasing. One such technology is the stabilized dispersive focal plane system (SDFPS). This technology provides image stabilization while simultaneously delivering spectroscopic or direct imaging functionality using only a single optical path and detector. Typical systems require multiple expensive optical trains and/or detectors, sometimes at the expense of photon throughput. The SDFPS is ideal for performing wide-field low-resolution space-based spectroscopic and direct-imaging surveys. In preparation for a suborbital flight, we have built and ground tested a prototype SDFPS that will concurrently eliminate unwanted image blurring due to the lack of adequate platform stability, while producing images in both spectroscopic and direct-imaging modes. We present the overall design, testing results, and potential scientific applications.

Ocean altimetry and wind applications of a GNSS nanosatellite constellation

Recent developments in electronics and nanosatellite technologies combined with modeling techniques developed over the past 20 years have enabled a new class of altimetry and wind remote sensing capabilities that offer markedly improved performance over existing observatories while opening avenues to new applications. Most existing spaceborne ocean altimetry and wind observatories are in polar low Earth orbits that maximize global coverage but result in either large gaps at the tropics or long time intervals between geolocation measurement revisits. This, combined with their use of radar systems operating in the C and Ku-bands, obscures key information about the ocean and the global climate. Using GNSS-based bi-static scatterometry performed by a constellation of nanosatellites in a non-polar low Earth orbit could provide ocean altimetry and wind data with unprecedented temporal resolution and spatial coverage across the full dynamic range of ocean wind speeds in all precipitating conditions – all with a system cost substantially less than existing and planned systems. This paper contrasts the performance of a GNSS nanosatellite constellation with the existing monolithic remote sensing observatories while identifying synergies of the systems that can be exploited to achieve a more complete understanding of both ocean current and wind phenomena. Two specific applications are reviewed; ocean winds and ocean wave altimetry. The recently awarded Cyclone Global Navigation Satellite System (CYGNSS) mission will be used for the ocean wind comparison while a notional GNSS constellation will be used for comparison of the ocean wave altimetry application. Design requirements, applications, and system implementation are presented for the GNSS nanosatellite constellation.

The nasa cygnss mission: Overview and status update

The NASA Earth Venture Cyclone Global Navigation Satellite System (CYGNSS) is a constellation of eight microsatellite observatories that was launched into a low (35°) inclination, low Earth orbit on 15 December 2016. Each observatory carries a 4-channel GNSS-R bistatic radar receiver. The radars are tuned to receive the L1 signals transmitted by GPS satellites, from which near-surface ocean wind speed is estimated. The mission architecture is designed to improve the temporal sampling of winds in tropical cyclones (TCs). The 32 receive channels of the complete CYGNSS constellation, combined with the ∼30 GPS satellite transmitters, results in a revisit time for sampling of the wind of 2.8 hr (median) and 7.2 hr (mean) at all locations between 38° North and 38° South latitude. Operation at the GPS L1 frequency of 1575 MHz allows for wind measurements in the TC inner core that are often obscured from other spaceborne remote sensing instruments by intense precipitation in the eye wall and inner rain bands. An overview of the CYGNSS mission is presented, followed by early on-orbit status and results.

Development of rotating prism mechanism and athermalized prism mounting for space

Space and launch environments demand robust, low mass, and thermally insensitive mechanisms and optical mount designs. The rotating prism mechanism (RPM), a component of the stabilized dispersive focal plane system (SDFPS), is a spectral disperser mechanism that enables the SDFPS to deliver spectroscopic or direct imaging functionality using only a single optical path. The RPM is a redundant, vacuum-compatible, self-indexing, motorized mechanism that provides robust, athermalized prism mounting for two sets of matching prisms. Each set is composed of a BK7 and a CaF2 prism, both 70 mm in diameter. With the prism sets separated by 1 mm, the RPM rotates the two sets relative to one another over a 180° range, and maintains their alignment over a wide temperature range (190-308K). The RPM design incorporates self-indexing and backlash prevention features as well as redundant motors, bearings, and drive trains. The RPM was functionally tested in a thermal vacuum chamber at 210K and <1.0x10-6 mbar, and employed in the top-level SDFPS system testing. This paper presents the mechanical design, analysis, alignment measurements, and test results from the prototype RPM development effort.

Software engineering processes for Class D missions

Software engineering processes are often seen as anathemas; thoughts of CMMI key process areas and NPR 7150.2A compliance matrices can motivate a software developer to consider other career fields. However, with adequate definition, common-sense application, and an appropriate level of built-in flexibility, software engineering processes provide a critical framework in which to conduct a successful software development project. One problem is that current models seem to be built around an underlying assumption of “bigness,” and assume that all elements of the process are applicable to all software projects regardless of size and tolerance for risk. This is best illustrated in NASA’s NPR 7150.2A in which, aside from some special provisions for manned missions, the software processes are to be applied based solely on the criticality of the software to the mission, completely agnostic of the mission class itself. That is, the processes applicable to a Class A mission (high priority, very low risk tolerance, very high national significance) are precisely the same as those applicable to a Class D mission (low priority, high risk tolerance, low national significance). This paper will propose changes to NPR 7150.2A, taking mission class into consideration, and discuss how some of these changes are being piloted for a current Class D mission—the Cyclone Global Navigation Satellite System (CYGNSS).