Nimbus design study, volume I Final report
Addendum to final report for Nimbus pulse code modulation design study
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Addendum to final report for Nimbus pulse code modulation design study
This Phase III final report summarizes the Phase I research and development work performed during the IRAD FY 2018-Cycle 1, Stage C-Phase I project March 15, 2018 through August 17, 2018 and during the Phase II continuation request which funded the research and development November 26, 2018 through September 30, 2019. A Phase III proposal was accepted to continue the technology development, but due to the unavailability of the Principal Investigators to complete the proposed PhasE III work, the Phase III project was re-scoped to complete a final report on the research and development work that was previously completed as a wrap-up of this IRAD project
This report is the final report of a SBIR Phase I project. It is identical to the final report submitted, after some proprietary information of administrative nature has been removed. The development of a numerical simulation tool for dielectric barrier discharge (DBD) plasma actuator is reported. The objectives of the project were to analyze and predict DBD operation at wide range of ambient gas pressures. It overcomes the limitations of traditional DBD codes which are limited to low-speed applications and have weak prediction capabilities. The software tool allows DBD actuator analysis and prediction for subsonic to hypersonic flow regime. The simulation tool is based on the VORPAL code developed by Tech-X Corporation. VORPAL's capability of modeling DBD plasma actuator at low pressures (0.1 to 10 torr) using kinetic plasma modeling approach, and at moderate to atmospheric pressures (1 to 10 atm) using hydrodynamic plasma modeling approach, were demonstrated. In addition, results of experiments with pulsed+bias DBD configuration that were performed for validation purposes are reported.
Performance of Mariner Mars 1969 mission by flight and Earth-based elements during launch and space flight phases - Vol. 2
This is the Performance Verification Report. the process specification establishes the requirements for the comprehensive performance test (CPT) and limited performance test (LPT) of the earth observing system advanced microwave sounding unit-A2 (EOS/AMSU-A2), referred to as the unit. The unit is defined on drawing 1356006.
This is the Final Report of a research project to investigate issues and provide guidance for the qualification of formal methods tools under the DO-330 qualification process. It consisted of three major subtasks spread over two years: 1) an assessment of theoretical soundness issues that may affect qualification for three categories of formal methods tools, 2) a case study simulating the DO-330 qualification of two actual tool sets, and 3) an investigation of risk mitigation strategies that might be applied to chains of such formal methods tools in order to increase confidence in their certification of airborne software.
Solar thermionic flight experiment final report - spacecraft design phase
This document represents the final report for the Joint Technical Architecture for Robotic Systems (JTARS) project, funded by the Office of Exploration as part of the Intramural Call for Proposals of 2005. The project was prematurely terminated, without review, as part of an agency-wide realignment towards the development of a Crew Exploration Vehicle (CEV) and meeting the near-term goals of lunar exploration.
This final report summarizes the results and accuracies of the Spitzer Space Telescope focal plane survey. Accuracies achieved are compared to the focal plane survey calibration requirements put forth in the SIRTF IOC-SV Mission Plan [14] and pre-flight predictions made in [2]. The results of this focal plane survey are presently being used to support in-flight precision pointing, precision incremental offsets, IRS peakup array calibration, and ground pointing reconstruction...
The Compass Final Report: Europa Tunnelbot, is a summary of three Compass concurrent engineering team designs for penetrating the ice of Europa and reaching the ocean, while sampling for biomarkers and communicating back to the surface. These conceptual designs, while providing complete conceptual layouts for these penetrators, or 'Tunnelbots' along with the associated communication 'Repeaters' primarily focused on the power and thermal systems needed for these devices. Trades for these systems will provide advantages and challenges for each option. These results will be used to guide power technology development.
This document is the final report of NRA contract NNC16CA39C that was conducted over the period September 2016 through November2019.This study leveraged hardware developed under NRAN+3 Combustor Technology Contract (NNC14CA30C)which developed, designed and tested a N+3, low-emissions, high-OPR compact combustor for a single-aisle advanced concept aircraft
The purpose of this document is to provide a final report on the Deorbit, Descent, and Landing (DDL) Tipping Point program, a public-private partnership between Blue Origin and NASA that is partially funded by NASA contract 80LARC19C0005. In this report we summarize the results of the entire contract, including recommendations and conclusions based on the experience and results obtained. Only the portions funded by the government with associated unlimited rights are documented in detail in this report. For the work funded by Blue Origin, summaries with unlimited rights are provided for context and completeness. The Blue Origin funded work exceeded 25% of the originally proposed total program cost and included a mixture of hardware procurement and critical technology maturation. The scope of this document is a discussion of all the major tasks performed under the contract including the sensor flight demonstrations on New Shepard, the hardware in the loop lunar landing navigator demonstration, and the ground testing of the Flash LiDAR hazard sensor. The contributions from the multiple NASA teams – Johnson Space Center, Langley Research Center, Goddard Space Flight Center, and Jet Propulsion Laboratory – are described along with the contributions from Blue Origin. This document is the Final Report for statement of work item 4.1.2.10 as Deliverable 5.8.
Mission analysis computer programs for evaluating nuclear engine, vehicle system, and mission parameters for nuclear propulsion system applications in 1975-1990
System analysis, system design, and equipment implementation for Airborne Range and Orbit determination /AROD/
Thermophysical properties of argon, oxygen, and nitrogen at cryogenic temperatures
This Final Report describes the actual studies conducted by four Summer Workshop teams. The problems they tackled were suggested by various Goddard activities. All scientific groups within GSFC were invited to submit problems which they desired to be investigated in-house by the Summer Workshop. The groups met with the principal investigator (a visiting professor) of each team in a pre-Workshop conference held in May. Priorities were assigned to the many items submitted and a study program was formulated. Among the principal factors which determined the areas selected for investigation were: the time element, the availability of professor-specialists representing particular disciplines, and the Center's ability to support the effort in providing needed facilities and work space.
This report is provided as part of ITT s NASA Glenn Research Center Aerospace Communication Systems Technical Support (ACSTS) contract NNC05CA85C, Task 7: New ATM Requirements-Future Communications, C-Band and L-Band Communications Standard Development and was based on direction provided by FAA project-level agreements for New ATM Requirements-Future Communications. Task 7 included two subtasks. Subtask 7-1 addressed C-band (5091- to 5150-MHz) airport surface data communications standards development, systems engineering, test bed and prototype development, and tests and demonstrations to establish operational capability for the Aeronautical Mobile Airport Communications System (AeroMACS). Subtask 7-2 focused on systems engineering and development support of the L-band digital aeronautical communications system (L-DACS). Subtask 7-1 consisted of two phases. Phase I included development of AeroMACS concepts of use, requirements, architecture, and initial high-level safety risk assessment. Phase II builds on Phase I results and is presented in two volumes. Volume I is devoted to concepts of use, system requirements, and architecture, including AeroMACS design considerations. Volume II (this document) describes an AeroMACS prototype evaluation and presents final AeroMACS recommendations. This report also describes airport categorization and channelization methodologies. The purposes of the airport categorization task were (1) to facilitate initial AeroMACS architecture designs and enable budgetary projections by creating a set of airport categories based on common airport characteristics and design objectives, and (2) to offer high-level guidance to potential AeroMACS technology and policy development sponsors and service providers. A channelization plan methodology was developed because a common global methodology is needed to assure seamless interoperability among diverse AeroMACS services potentially supplied by multiple service providers.
This paper presents a final report on sounding rocket flight activity. The period of performance is from 11 February 1997 to 31 January 2000.