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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

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At least 1,333 records · Page 74

SmallSat Spinning Lander with a Raman Spectrometer Payload for Future Ocean Worlds Exploration Missions

We describe an Evolved Expendable Launch Vehicle Secondary Payload Adapter (ESPA)-class SmallSat spinning lander concept for the exploration of Europa or other Ocean World surfaces to ascertain the potential for life. The spinning lander will be ejected from an ESPA ring from an orbiting or flyby spacecraft and will carry on-board a standoff remote Spatial Heterodyne Raman spectrometer (SHRS) and a time resolved laser induced fluorescence spectrograph (TR-LIFS), and once landed and stationary the instruments will make surface chemical measurements. The SHRS and TR-LIFS have no moving parts have minimal mass and power requirements and will be able to characterize the surface and near-surface chemistry, including complex organic chemistry to constrain the ocean composition.

Ridenoure, R.↗

Cell Science 2 (CS-02) Payload Overview

This payload overview presentation will be presented at the POIWG on October 17th, 2017. It provides a high-level overview of Cell Science-02 operations.

Cell Scienc↗

Control and Non-Payload Communications (CNPC) Prototype Radio Verification Test Report

This report provides an overview and results from the verification of the specifications that defines the operational capabilities of the airborne and ground, L Band and C Band, Command and Non-Payload Communications radio link system. An overview of system verification is provided along with an overview of the operation of the radio. Measurement results are presented for verification of the radios operation.

avionics↗

Control and Non-Payload Communications (CNPC) Prototype Radio Validation Flight Test Report

This report provides an overview and results from the unmanned aircraft (UA) Control and Non-Payload Communications (CNPC) Generation 5 prototype radio validation flight test campaign. The radios used in the test campaign were developed under cooperative agreement NNC11AA01A between the NASA Glenn Research Center and Rockwell Collins, Inc., of Cedar Rapids, Iowa. Measurement results are presented for flight tests over hilly terrain, open water, and urban landscape, utilizing radio sets installed into a NASA aircraft and ground stations. Signal strength and frame loss measurement data are analyzed relative to time and aircraft position, specifically addressing the impact of line-of-sight terrain obstructions on CNPC data flow. Both the radio and flight test system are described.

Shalkhauser, Kurt A.↗

Sandwich Structure Risk Reduction in Support of the Payload Adapter Fitting

Reducing risk for utilizing honeycomb sandwich structure for the Space Launch System payload adapter fitting includes determining what parameters need to be tested for damage tolerance to ensure a safe structure. Specimen size and boundary conditions are the most practical parameters to use in damage tolerance inspection. The effect of impact over core splices and foreign object debris between the facesheet and core is assessed. Effects of enhanced damage tolerance by applying an outer layer of carbon fiber woven cloth is examined. A simple repair technique for barely visible impact damage that restores all compression strength is presented.

Nettles, A. T.↗

MagicDraw Report Generation for the Resource Prospector Payload

Magic Draw is a tool currently being used by System Engineers to design model-based representations of the Resource Prospector (RP) Payload. Often, reports are needed to display and communicate the information and schematics within the MagicDraw model. Since constant changes are being made to the model, these reports also need to be maintained with each change. Because this is tedious and time consuming, I was assigned to implement MagicDraw Report Wizard Templates using Velocity Template Language (VTL) scripts. These report template scripts pull specific images, data, and elements directly from the MagicDraw model, allowing the user to have a report that is updated with the current state of the model upon its generation.

MagicDraw↗

Repair of Sandwich Structure in Support of the Payload Adapter Fitting

As part of a program examining a composite payload adaptor fitting (PAF) for NASA’s Space Launch System (SLS), a repair study of impact damage and misdrilled holes was undertaken. At the beginning of this repair study, the PAF was baselined as a honeycomb sandwich structure with eight-ply quasi-isotropic, carbon-fiber-reinforced epoxy facesheets. Although the baseline configuration could change, the repair program presented herein is generic enough in nature such that it will apply to most sandwich configurations. The vast majority of loads experienced by this structure will be in-plane compression; thus, this repair study concentrates on the in-plane compression strength of representative sandwich structure specimens. The PAF is a truncated cone with a minimum diameter of about 170 inches at the top and a maximum diameter of about 335 inches at the bottom. While the launch vehicle hardware should be protected throughout its life on the ground, rogue events (or misdrilled holes) are still a possibility. This study is not meant to address large scale damage or damage to the part other than in the acreage (the uniform portion of the structure that does not consist of joints or other detailed areas), but address the most probable type of damages (small impacts and misdrilled holes) in the vast majority of the structure (the acreage).

Nettles, A. T.↗

Real-Time Data Products and the Intelligent Payload Module

This presentation goes over the last 10 years of effort to prototype various aspects fo the HyspIRI Intelligent Payload Module (IPM). This was a mission requirement and various protoytpe efforts were conducted to bring risk down. The effort goes over various hardware and software protoytpe efforts.

high performance space computing↗

Reducing Hazards of Propulsive Secondary Payloads by Implementing a Post Launch Pressurization System

Propulsion systems on SmallSats and CubeSats are becoming more common as launch vehicles like SLS begin providing rideshares to destinations beyond low earth orbit. While these spacecraft are a solution to achieve advanced science objectives at lower cost, they are still subject to the same rigorous standards as other larger spacecraft, such as NASA STD-5019, due to the high pressures within their propulsion systems at launch. A Post Launch Pressurization System would allow a spacecraft to be launched at low pressure, then be pressurized through the controlled chemical decomposition of a solid reactant after the spacecraft is jettisoned from the launch vehicle. This increases the safety of the secondary spacecraft, and effectively mitigates risks to the launch vehicle and other payloads.

Perry, McKynzie↗

Telemetry Options for LDB Payloads

The Columbia Scientific Balloon Facility (CSBF) provides Telemetry and Command systems necessary for balloon operations and science support. There are various Line-Of-Sight (LOS) and Over-The-Horizon (OTH) systems and interfaces that provide communications to and from a science payload. This presentation will discuss the current data throughput options available and future capabilities that are planned to be incorporated in the CSBF Science Support Systems such as 8Mbps LOS data and up to 1Mbps OTH data.

LDB↗

Single-Event Latchup Measurements on COTS Electronic Devices for Use in ISS Payloads

This paper reports recent single-event latchup results for a variety of microelectronic devices that include an ADC, OpAmp, EEPROM, CPLD, PWM, transceiver, voltage regulator, digital signal processor, step-down converter, buck controller and supervisory circuits. The data were collected to evaluate these devices for possible use in NASA ISS payloads.

Irom, Farokh↗

Mars Ascent Vehicle - Payload?, Spacecraft?, Launch Vehicle? - A Systems Approach to MAV

Significant effort has been expended over the past few years in order to examine propulsion technologies for an eventual robotic Mars Ascent Vehicle (MAV). The recent emphasis on studies for an overall sample return campaign, and specifically the Sample Return Lander (SRL) includes the full slate of systems required to implement a MAV. Depending on your point of view, the MAV is a major SRL flight system payload, a Mars Surface Spacecraft, or a Launch Vehicle. We will examine the MAV from these three perspectives in order to tease out the key architectural trades required to be completed prior to the start of a project Phase A activity.

Jackman, Angie↗

Flow Boiling and Condensation Experiment: Payload Design Overview

The Flow Boiling and Condensation Experiment (FBCE) is a flight experiment that is designed to operate in the Fluids Integrated Rack (FIR) on the International Space Station (ISS). The objective of the FBCE is to develop an integrated two-phase flow experiment that will serve as a primary platform for obtaining flow boiling and condensation heat transfer data in microgravity. This presentation discusses the overall design of the FBCE payload, as well as the status of the FBCE hardware as it continues through final verification testing.

Guzik, Monica C.↗

Repair of Sandwich Structure in Support of the Payload Adapter Fitting (PAF) Part II: Severe Damage Repair

As part of a program examining a Payload Adaptor Fitting (PAF) for NASA’s Space Launch System (SLS), a repair study of impact damage and misdrilled holes in composite sandwich structure was undertaken.1 In that study, it was shown that small holes and barely visible impact damage (BVID) could be repaired and all the measured undamaged in-plane compression strength recovered without removing the damaged material using a simple patch repair. It was noted that for more severe damage, either larger patches or removal of damage (or both) may be necessary to regain all of the measured undamaged compression strength. This Technical Memorandum (TM) presents the results of an experimental investigation into repair of more severely damaged sandwich structure than what was studied in reference 1.

Nettles, A. T.↗

History and Logic Model NASA Goddard Space Flight Center Instrument and Payload Systems Engineering Technical Performance Study

Historically, some NASA missions have exceeded schedule and cost commitments. Studies suggest technical performance is a contributor. The 1980 NASA Project Management Study concluded, "one of the most significant contributors to cost and schedule growth is inadequate definition of technical and management aspects of a program..." (as cited in GAO/NSIAD-93-97, p. 11). The 1991 NASA Roles and Missions Report identified a "need for increased emphasis on technological readiness and requirements on the front end of a program" (as cited in GAO/NSIAD-93-97, p. 11). The 1992 NASA Program Costs Report stated that NASA officials identified, among other things, "insufficient definition studies... [and] program redesigns and technical complexities" as reasons for cost and schedule overruns (GAO/NSAID-93-97, p. 11). The 2002 Task Force on Acquisition of National Security Space Programs found "requirements definition and control issues, unhealthy cost bias in proposal evaluation, widespread lack of budget reserves required to implement high risk programs on schedule, and an overall underappreciation of the importance of appropriately staffed and trained system engineering staff to manage the technologically demanding and unique aspects of space programs" (DoD, 2003, p.i.) In 2007, The NASA Office of the Chief Engineer chartered the NASA Instrument Capability Study (NICS) “to determine whether NASA instrument developers are facing challenges that impact the capability to design and build quality instruments or whether there are flaws in the acquisition strategy evidenced by schedule delays, cost overruns, and increased technical risk via design deficiencies. The... team was also chartered to determine if occurrences [are]... isolated cases or if there are generic issues... If the issues [are] found to be generic, the team [is] to offer solutions to recover such capability" (NICS Report, 2008, p. vi). The 2008 NICS Report, led by Goddard Space Flight Center (GSFC), identified challenges to instrument technical performance consistent with findings from previous reports. In 2017, the Instrument Project Division (IPD) Implementation Study was initiated to determine if there was a change in meeting schedule and cost commitments after implementing certain NICS recommendations. In 2018, the Instrument Technical Performance Study was initiated to determine the current state of Instrument Technical Performance in the GSFC Payload & Instrument Systems Engineering Branch. The purpose of the combined studies is to answer the question, "Is there a relationship between meeting NASA scientific instrument technical success and meeting schedule and cost commitments? If yes, what is the relationship?" References Department of Defense Office of the Under Secretary of Defense for Acquisition, Technology, and Logistics. (2003). The report of the defense science board/ air force scientific advisory board joint task force on acquisition of national security space programs. Washington DC. Government Accounting Office. (1992). NASA program costs: Space missions require substantially more funding than initially estimated. GAO/NSIAD-93-97. Washington DC. National Aeronautics and Space Administration, National Oceanic and Atmospheric Agency, Department of Defense. (2008). The NASA instrument capability study final report. NP-2008-11-058-GSFC. Washington DC.

Robbins, Geraldine↗

Design Considerations and Development Status for Atmospheric Powered Descent of High-Mass Payloads at Mars

Retropropulsion, initiated at supersonic conditions, is the only presently viable approach to the descent and landing of human-scale payloads on Mars, providing both deceleration and control authority for precision landing. Atmospheric powered descent challenges traditional processes and dependencies in system design. Changes to a design by one discipline have a greater potential to affect overall vehicle performance than in the case of powered descent with no atmosphere. The interdependence is due to the sensitivity of propulsive-aerodynamic interference effects to small changes in configuration or operational environment. The fidelity of Mars exploration architectures has increased in recent years, and the conditions and designs with the lowest aerosciences uncertainties are no longer as flight-relevant. At this time, there is no human-rated vehicle relying on retropropulsion for descent and landing in an atmospheric environment. Continued development of powered descent for atmospheric environments is enabled by progressive balanced investments in ground testing, predictive computational capabilities, and flight testing and demonstration.

EDL↗