Standards for mission operations documentation

Tomorrow marks 5 years since the Curiosity rover’s dramatic landing on the red planet! The rover’s Sample Analysis at Mars (SAM) instrument suite onboard Curiosity is the most complicated instrument NASA has ever sent to another planet. SAM is designed to measure the composition of the atmosphere and solid samples inside Gale Crater on Mars, and help scientists assess the habitability (could a certain place support life?) of environments recorded in in rocks in Gale Crater. The SAM team has made many amazing discoveries, including finding evidence of a habitable environment – a place that life (think tiny microorganisms, not dinosaurs) could have survived if it had been in that spot on Mars, millions of years ago. SAM also detected the first organics (building blocks of life) on Mars, known to have originated on this planet. We’re a group of scientists and engineers from the SAM team, ready to answer your questions about Mars and SAM. We’ll be online from 1:00 to 2:00 pm EST and we will sign our answers. Ask us anything! Paul Mahaffy, SAM Principle Investigator, Director of Solar System Exploration Division, NASA Goddard Space Flight Center Charles Malespin, SAM Deputy Principle Investigator, NASA Goddard Space Flight Center Jen Stern, Planetary Scientist, NASA Goddard Space Flight Center James Lewis, Postdoctoral Fellow, NASA Goddard Space Flight Center Brad Sutter, Planetary Scientist, NASA Johnson Space Flight Center Greg Flesch, Instrument Engineer, NASA Jet Propulsion Laboratory Peter Martin, PhD student, CalTech/NASA Jet Propulsion Laboratory Doug Archer, Planetary Scientist/NASA Johnson Space Center We have now been on Mars for 5 years - WOW. The first year after landing we actually played the Happy Birthday song using our SSIT (solid sample inlet tube). You may find this link interesting https://www.youtube.com/watch?v=uxVVgBAosqg EDIT It has been great answering your questions, we are signing off now!

The Glory program is an Earth and Solar science mission designed to broaden science community knowledge of the environment. The causes and effects of global warming have become a concern in recent years and Glory aims to contribute to the knowledge base of the science community. Glory is designed for two functions: one is solar viewing to monitor the total solar irradiance and the other is observing the Earth's atmosphere for aerosol composition. The former is done with an active cavity radiometer, while the latter is accomplished with an aerosol polarimeter sensor to discern atmospheric particles. The Glory program is managed by NASA Goddard Space Flight Center (GSFC) with Orbital Sciences in Dulles, VA as the prime contractor for the spacecraft bus, mission operations, and ground system. This paper describes some of the more unique features of the Glory program including the integration and testing of the satellite and instruments as well as the science data processing. The spacecraft integration and test approach requires extensive analysis and additional planning to ensure existing components are successfully functioning with the new Glory components. The science mission data analysis requires development of mission unique processing systems and algorithms. Science data analysis and distribution will utilize our national assets at the Goddard Institute for Space Studies (GISS) and the University of Colorado's Laboratory for Atmospheric and Space Physics (LASP). The satellite was originally designed and built for the vegetation canopy lidar (VCL) mission, which was terminated in the middle of integration and testing due to payload development issues. The bus was then placed in secure storage in 2001 and removed from an environmentally controlled container in late 2003 to be refurbished to meet the Glory program requirements. Functional testing of all components was done as a system at the start of the program, very different from a traditional program. The plan for Glory is to minimize any changes to the spacecraft in order to meet the Glory requirements. This means that the instrument designs must adhere to the existing interfaces and capabilities as much as possible. Given Glory's unique history and the potential science return, the program is one of significant value to both the science community and the world. The findings Glory promises will improve our understanding of the drivers for global climate change for a minimal investment. The program hopes to show that reuse of existing government assets can result in a lower cost, and a fully successful mission.

A software production model is developed that integrates process and product and is designed to identify bottlenecks in the production process. Choke points can occur either from process deficiencies or failure to identify and correct extant software defects. NASA Goddard Space Flight Center satellite defect data is used in the analysis because the primary aim is to apply the model to safety critical software. The model applies feedback control to correct anomalies in process and product that may occur. Both predictions and actual defect data are used to identify process and product behavior that do not meet expectations. I. Introduction A CCORDING to, 1 software systems come and go through a series of passages that account for their inception, initial development, productive operation, upkeep, and retirement from one generation to another. We focus on the development and production phases and introduce something different in this research compared with articles about software development process that correctly relate the effectiveness of the process to the quality of the product. We go a step further and introduce the concept of the reliability of the process, both current and future. We perform this analysis by using software defect data from the NASA Goddard Space Flight Center satellite project known as JM1. These data are shown in Table 1. Our goal, recognizing the importance of integrating process and product, 2 is to identify production bottlenecks in the process that cause product delivery to be delayed. In addition, we identify deficiencies in the defect removal process that can lead to product unreliability and delivery schedule delay. The principal features of the production system are defined using process flow charts illustrated in Fig. 1 for a software production and quality control operation. The flow of software modules is from left to right. Each phase has a processing time measured in days and a defect rate. Our model assumes that defects introduced by a process step may pass through downstream steps undetected until an inspection is performed. 3

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With a view towards reducing cost and complexity for spacecraft early mission support at the NASA Goddard Space Flight Center (GSFC), efforts are being made to automate the attitude sensor calibration process. This paper addresses one of the major components needed by such a system. The beneficiaries of an improved calibration process are missions that demand moderate to high precision attitude knowledge or that need to perform accurate attitude slews. Improved slew accuracy reduces the time needed for re-acquisition of fine-pointing after each attitude maneuver, Rapid target acquisition can be very important for astronomical targeting or for off-nadir surface feature targeting by Earth-oriented spacecraft. The normal sequence of on-orbit calibration starts with alignment calibration of the star trackers and possibly the Sun sensor. Their relative alignment needs to be determined using a sufficiently large data set so their fields of view are adequately sampled. Next, the inertial reference unit (IRU) is calibrated for corrections to its alignment and scale factors. The IRU biases are estimated continuously by the onboard attitude control system, but the IRU alignment and scale factors are usually determined on the ground using a batch-processing method on a data set that includes several slews sufficient to give full observability of all the IRU calibration parameters. Finally, magnetometer biases, alignment, and its coupling to the magnetic torquers are determined in order io improve momentum management and occasionally for use in the attitude determination system. The detailed approach used for automating calibrations will depend on whether the automated system resides on the ground or on the spacecraft with an ultimate goal of autonomous calibration. Current efforts focus on a ground-based system driving subsystems that could run either on the ground or onboard. The distinction is that onboard calibration should process the data sequentially rather than in a single large batch since onboard computer data storage is limited. Very good batch- processing calibration utilities have been developed and used extensively at NASA/GSFC for mission support but no sequential calibration utilities are available. To meet this need, this paper presents the mathematical description of a sequential IRU calibration system. The system has been tested using flight data from the Rossi X-ray Timing Explorer (RXTE) during a series of attitude slews. The paper also discusses the current state of the overall automated system and describes plans for adding sequential alignment calibration and other additions that will reduce the amount of analyst time and input.

This paper presents radiation effects characterization performed by the NASA Goddard Space Flight Center (GSFC) on spaceflight candidate 16 Mbit DRAMs. This includes heavy ion, proton, and Co/sup 60/ irradiations on single-chip devices as well as proton irradiation of a stacked DRAM module. Lastly, a discussion of test methodology is undertaken.

Autonomic computing for spacecraft ground systems increases the system reliability and reduces the cost of spacecraft operations and software maintenance. In this paper, we present an autonomic computing solution for spacecraft ground systems at NASA Goddard Space Flight Center (GSFC), which consists of an open standard for the message oriented architecture referred to as GMSEC architecture, the GSFC Mission Services Evolution Center, and an autonomic computing tool, Criteria Action Table (CAT). This solution has been used in many upgraded ground systems for NASA's missions, and provides a framework for developing solutions with higher autonomic maturity.

Engineering Design and Development DivisionScientific and Commercial Systems CorporationAlexandria, VirginiaABSTRACTThe historically high toll in human lives lost to natural disasters such as hurricanes, tornadoes, floods, and otherprogressive events signals the need for some type of personal warning that alerts people to the need to evacuateor otherwise protect themselves in the face of an advancing threat. Traditional warning services, which rely onbroadcasts by the mass media in the metropolitan areas of the United States, achieve measurable success indisseminating warnings. However, warnings to isolated populations that exist in the U.S. and elsewhere in theworld may be poor to effectively nonexistent, especially in the many archipelagoes. Earth Alert, a joint projectof NASA Goddard Space Flight Center (GSFC) and Scientific and Commercial Systems Corporation (SCSC), istargeted at development of a simple, low-cost means for providing timely warning to otherwise isolated popula-tions. The project uses appropriate relay capabilities of U.S. satellites already in orbit, and thus avoids the high-cost development and launch of dedicated resources.Key words: GOES, emergency warning, WEFAX, repeater1. INTRODUCTIONIn an August 13, 1992 meeting with SCSC managers, the Chief of NASA GSFC International Data SystemsOffice raised the idea of a technology transfer project to provide timely personal warning to isolated populationsthreatened by natural disaster. The specific suggestion was that some capabilities of on-orbit satellite systemscould be diverted to provide enough warning to permit these populations to prepare for the threat of naturaldisasters such as hurricanes, tornadoes, orfloods. The NASA official was armed witha wealth ofexamples ofserious weather

The Formation Flying Test Bed (FFTB) at NASA Goddard Space Flight Center (GSFC) is being developed as a modular, hybrid dynamic simulation facility employed for end-to-end guidance, navigation, and control (GN&C) analysis and design for formation flying clusters and constellations of satellites. The FFTB will support critical hardware and software technology development to enable current and future missions for NASA, other government agencies, and external customers for a wide range of missions, particularly those involving distributed spacecraft operations. The initial capabilities of the FFTB are based upon an integration of high fidelity hardware and software simulation, emulation, and test platforms developed at GSFC in recent years; including a high-fidelity GPS simulator which has been a fundamental component of the Guidance, Navigation, and Control Center's GPS Test Facility. The FFTB will be continuously evolving over the next several years from a tool with initial capabilities in GPS navigation hardware/software-in-the-loop analysis and closed loop GPS-based orbit control algorithm assessment to one with cross-link communications and relative navigation analysis and simulation capability. Eventually the FFTB will provide full capability to support all aspects of multi-sensor, absolute and relative position determination and control, in all (attitude and orbit) degrees of freedom, as well as information management for satellite clusters and constellations. In this paper we focus on the architecture for the FFTB as a general GN&C analysis environment for the spacecraft formation flying community inside and outside of NASA GSFC and we briefly reference some current and future activities which will drive the requirements and development.

The NASA Goddard Space Flight Center (GSFC) High-altitude Imaging Wind and Rain Airborne Profiler (HIWRAP) is a solid-state dual frequency Doppler radar funded by the NASA Instrument Incubator Program. It uses direct-digital-synthesizer devices to generate versatile waveforms including conventional pulses and linear frequency modulation (LFM) chirps. This letter describes a waveform used by the GSFC and the Remote Sensing Solutions to address the critical limitations of range sidelobes and blind ranges in airborne pulse-compression radar. By utilizing a frequency diversity waveform consisting of two pulses and an LFM chirp at each transmit cycle, this system provides the improved sensitivity and range resolution benefits of pulse compression on targets within the middle and high altitudes while maintaining conventional pulsed data near the radar and the surface. The data obtained by the HIWRAP during the NASA Midlatitude Continental Convective Clouds Experiment using this waveform scheme are presented.

The trade-off between spectral resolution and instrument throughput is analyzed for a compact, uncooled, longwave infrared (LWIR) channeled spectropolarimeter (IRCSP). The IRCSP was developed as a part of the Sub-mm Wave and InfraRed Polarimeters (SWIRP) project out of NASA's Goddard Spaceflight Center. The IRCSP scientific objective targets measurements of AOLP and DOLP with 1-µm spectral resolution from 8.5 - 12.5µm in a single snapshot. The geometry of the field stop determines the field of view (FOV) of the IRCSP. This work relates the spectral resolution, instrument throughput, and polarimetric accuracy of a spectro-polarimeter to the FOV. The accuracy of linear Stokes retrievals for low temperature thermal targets are predicted for varying FOV and measurement noise conditions. This work presents a method to quantify the achievable accuracy in AOLP and DOLP as a function of field stop dimensions and signal-to-noise ratio (SNR). While smaller field stops are shown to improve accuracy as the spectral resolution is increased, low SNR is the dominant source of error for the IRCSP prototype. For the IRCSP, a SNR of at least 80 is required to produce DOLP measurements with < 5% error for targets with DOLP < 0.2.

The General Mission Analysis Tool (GMAT) is an open-source space mission design, analysis and trajectory optimization tool. GMAT is developed by a team of NASA, private industry, public and private contributors. GMAT is designed to model, optimize and estimate spacecraft trajectories in flight regimes ranging from low Earth orbit to lunar applications, interplanetary trajectories and other deep space missions. GMAT has also been flight qualified to support operational maneuver planning for the Advanced Composition Explorer (ACE) mission. ACE was launched in August, 1997 and is orbiting the Sun-Earth L1 libration point. The primary science objective of ACE is to study the composition of both the solar wind and the galactic cosmic rays. Operational orbit determination, maneuver operations and product generation for ACE are conducted by NASA Goddard Space Flight Center (GSFC) Flight Dynamics Facility (FDF). This paper discusses the entire engineering lifecycle and major operational certification milestones that GMAT successfully completed to obtain operational certification for the ACE mission. Operational certification milestones such as gathering of the requirements for ACE operational maneuver planning, gap analysis, test plans and procedures development, system design, pre-shadow operations, training to FDF ACE maneuver planners, shadow operations, Test Readiness Review (TRR) and finally Operational Readiness Review (ORR) are discussed. These efforts have demonstrated that GMAT is flight quality software ready to support ACE mission operations in the FDF.

Due to high launch vehicle costs, space instrumentation designers are constantly pressured to decrease weight and increase reliability of flight hardware. To meet these needs in a spectrometer, the infrared products team at Optical Coating Laboratory, Inc. (OCLI) and the NASA Goddard Space Flight Center (GSFC) have developed an infrared logarithmically variable filter for use in NASA's Pluto Fast Fly-by instrument. The filter and diode array combination replaces the multiple optical elements in conventional spectrometers, resulting in lower instrumentation weight and complexity with no moving parts. The choice of logarithmic rather than linear profile yields constant resolving power on every pixel of the array. Filters were produced in which the center wavelength varied from 1.0-1.581 micrometers , and 1.581-2.5 micrometers over a distance of 1.024 cm. Bandwidth was 0.3% FWHM and overall transmittance ranged from 30% to 50%. This paper discusses the major issues and tradeoffs in the design, manufacture, and testing of the filters. Measurement techniques are presented and comparisons are made between theoretical and measured performance of bandwidth, transmittance, and spectral profile.

An application of the Design Structure Matrix to Integrated Concurrent Engineering

X-ray astronomy critically depends on X-ray optics. The capability of an X-ray telescope is largelydetermined by the point-spread function (PSF) and the photon-collection area of its mirrors, the same astelescopes in other wavelength bands. Since an X-ray telescope must be operated above the atmosphere inspace and that X-rays reflect only at grazing incidence, X-ray mirrors must be both lightweight and thin, bothof which add significant technical and engineering challenge to making an X-ray telescope. In this paper wereport our effort at NASA Goddard Space Flight Center (GSFC) of developing an approach to making an Xraymirror assembly that can be significantly better than the mirror assembly currently flying on the ChandraX-ray Observatory in each of the three aspects: PSF, effective area per unit mass, and production cost per uniteffective area. Our approach is based on the precision polishing of mono-crystalline silicon to fabricate thinand lightweight X-ray mirrors of the highest figure quality and micro-roughness, therefore, having thepotential of achieving diffraction-limited X-ray optics. When successfully developed, this approach will makeimplementable in the 2020s and 2030s many X-ray astronomical missions that are currently on the drawingboard, including sounding rocket flights such as OGRE, Explorer class missions such as STAR-X andFORCE, Probe class missions such as AXIS, TAP, and HEX-P, as well as large missions such as Lynx.