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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 91 records · Page 5
All sourcesNASA NTRSDOE OSTI
NASA NTRS1990

Project SPARC: Space-Based Aeroassisted Reusable Craft

Future United States' space facilities include a Space Station in low Earth orbit (LEO) and a Geosynchronous Operations Support Center, or GeoShack, in geosynchronous orbit (GEO). One possible mode of transfer between the two orbits is an aerobraking vehicle. When traveling from GEO to LEO, the Earth's atmosphere can be used to aerodynamically reduce the velocity of the vehicle, which reduces the amount of propulsive change in velocity required for the mission. An aerobrake is added to the vehicle for this purpose, but the additional mass increases propellant requirements. This increase must not exceed the amount of propellant saved during the aeropass. The design and development of an aerobraking vehicle that will transfer crew and cargo between the Space Station and GeoShack is examined. The vehicle is referred to as Project SPARC, a SPace-based Aeroassisted Reusable Craft. SPARC consists of a removable 45 ft diameter aerobrake, two modified Pratt and Whitney Advanced Expander Engines with a liquid oxygen/liquid hydrogen propellant, a removable crew module with a maximum capacity of five, and standard sized payload bays providing a maximum payload capacity of 28,000 lbm. The aerobrake, a rigid, ellipsoidally blunted elliptical cone, provides lift at zero angle-of-attack due to a 73 deg rake angle, and is covered with a flexible multi-layer thermal protection system. Maximum dry mass of the vehicle without payload is 20,535 lbm, and the maximum propellant requirement is 79,753 lbm at an oxidizer to fuel ratio of 6/1. Key advantages of SPARC include its capability to meet mission changes, and its removable aerobrake and crew module.

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NASA NTRS1972

Impact of low cost refurbishable and standard spacecraft upon future NASA space programs. Payload effects follow-on study

The study has concluded that there are very large space program cost savings to be obtained by use of low cost, refurbishable, and standard spacecraft in conjunction with the shuttle transportation system. The range of space program cost savings for three different groups of programs are shown in quantitative terms. The total savings for the 91 programs will range from $13.4 billion to $18.0 billion depending on the degree of hardware standardization. These savings, principally resulting from payload cost reductions, tangibly support the development costs of the shuttle system.

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NASA NTRS2025

Enhancing Nasa Sounding Rocket Capabilities Through Composite Material Adoption

Sounding rockets are a suborbital research platform employed by NASA for heliophysics, astrophysics, and geospace science investigations, and for technology development. They follow semi-parabolic trajectories and are launched using surplus military, and commercial, solid-propellant rocket motors. NASA sounding rocket payloads are comprised of standard, modular subassemblies, designed to perform specific functions critical to achieving mission success criteria. Since the program’s inception, payload length and mass have trended upwards, limiting the capability of the platform to reach exospheric apogees and decreasing the time above critical altitudes to observe solar and celestial targets. To offset this trend, composite materials may be of use in payload and subsystem design to decrease payload mass. This investigation seeks to understand if there is a practical benefit to introducing composite materials on the NSRP by assessing mission specific impacts to those missions conducted in fiscal year 2024. To accurately estimate the mass of a composites-based payload, a standard subsystem (NIACS) underwent structural reconfiguration. Materials were selected that align with NSRP design, manufacturing, and testing standards. NIACS reconfiguration resulted in a mass reduction of 19.6% which was then applied to the payload system in entirety. Using vehicle performance carpet plots, delta apogee and time above the Kármán line were determined. Performance improvements were then evaluated against that mission’s success criteria to determine if that mission would have benefitted from using composite materials. On average, each mission would have gained 59.8 kilometers apogee and 62.9 seconds above the Kármán line. However, only nine of the seventeen missions would have benefitted from these performance improvements. Two of the missions could have used a lower-impulse launch vehicle to achieve mission success. Upleg stability met programmatic criteria; downleg instability and dynamic pressure improved, showing that ballast would not offset the mass reduction of using composite materials. Cost analysis showed that production costs will increase 39%. For the two missions that could have used a lower-impulse launch vehicle, the cost of the launch vehicle would have offset payload production costs. In summary, composite materials are not recommended for universal use on NASA sounding rocket payloads due to unclear programmatic benefits and added cost. However, they are justified for optical astrophysics and heliophysics missions, high-apogee (exosphere) requirements, or when they reduce payload costs versus higher impulse launch vehicles. Reflown, recoverable subsystems should use composites to enhance apogee and observation time.

Robert Henry Burth↗
NASA NTRS1977

NASA's standard spacecraft for free flying shuttle payloads

The paper gives a detailed description of the Multimission Modular Spacecraft. Attention is given to the structural system, the electrical system, the thermal control system, the power system, attitude control, the propulsion module, and mission considerations.

Bartlett, R. O.↗
NASA NTRS2014

Enhanced International Space Station Ku-Band Telemetry Service

(1) The ISS is diligently working to increase utilization of the resources this unique laboratory provides; (2) Recent upgrades enabled the use of Internet Protocol communication using the CCSDS IP Encapsulation protocol; and (3) The Huntsville Operations Support Center has extended the onboard LAN to payload teams enabling the use of standard IP protocols for payload operations.

Cecil, Andrew↗
NASA NTRS1972

Impact of low cost refurbishable and standard spacecraft upon future NASA space programs. Payload effects follow-on study, appendix

Mission analysis is discussed, including the consolidation and expansion of mission equipment and experiment characteristics, and determination of simplified shuttle flight schedule. Parametric analysis of standard space hardware and preliminary shuttle/payload constraints analysis are evaluated, along with the cost impact of low cost standard hardware.

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NASA NTRS1976

Payload specialist station study. Volume 3: Program study cost estimates. Part 1: Work breakdown structure

The work breakdown structure (WBS) for the Payload Specialist Station (PSS) is presented. The WBS is divided into two elements--PSS contractor and mission unique requirements. In accordance with the study ground rules, it is assumed that a single contractor, hereafter referred to as PSS Contractor will perform the following: (1) provide C and D hardware (MFDS and elements of MMSE), except for GFE; (2) identify software requirements; (3) provide GSE and ground test software; and (4) perform systems engineering and integration in support of the Aft Flight Deck (AFD) C and D concept. The PSS Contractor WBS element encompasses a core or standardized PSS concept. Payload peculiar C and D requirements identified by users will originate as a part of the WBS element mission unique requirements; these requirements will be provided to the PSS Contractor for implementation.

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NASA NTRS1977

Life science payloads planning study

Preferred approaches and procedures were defined for integrating the space shuttle life sciences payload from experiment solicitation through final data dissemination at mission completion. The payloads operations plan was refined and expended to include current information. The NASA-JSC facility accommodations were assessed, and modifications recommended to improve payload processing capability. Standard format worksheets were developed to permit rapid location of experiment requirements and a Spacelab mission handbook was developed to assist potential life sciences investigators at academic, industrial, health research, and NASA centers. Practical, cost effective methods were determined for accommodating various categories of live specimens during all mission phases.

Nelson, W. G.↗
NASA NTRS2012

An Evaluation of Protocol Enhancing Proxies and File Transport Protocols for Satellite Communication

NASA is utilizing Global Hawk aircraft in high-altitude, long-duration Earth science missions. Communications with the onboard research equipment and sensors (the science payload) is via Ku-Band radio utilizing satellites in geostationary orbits. All payload communications use standard Internet Protocols and routing, and much of the data to be transferred is comprised of very large files. The science community is interested in fully utilizing these communication links to retrieve data as quickly and reliably as possible. A test bed was developed at NASA Ames to evaluate modern transport protocols as well as Protocol Enhancing Proxies (PEPs) to determine what tools best fit the needs of the science community. This paper describes the test bed used, the protocols, the PEPs that were evaluated, the particular tests performed and the results and conclusions.

Finch, Patrick Eugene↗
NASA NTRSDate not supplied

On-orbit Servicing, Assembly and Manufacturing (OSAM) Near-Term in-Space Developmental Test Persistent Platform: ESPA-Star Based Implementation

Roundtable Session on In-Space Developmental Test: Springboard for Rapid Development. Presentation is a brief description of the On-orbit Servicing Assembly & Manufacturing (OSAM) national initiative & using standard EELV Secondary Payload Adapters (ESPAs) as the core building block to construct an ESPA-Star based implementation for an iSDT persistent platform in space.

Persistent Platform↗
NASA NTRS1984

Orbiter middeck/payload standard interfaces control document

The interfaces which shall be provided by the baseline shuttle mid-deck for payload use within the mid-deck area are defined, as well as all constraints which shall be observed by all the users of the defined interfaces. Commonality was established with respect to analytical approaches, analytical models, technical data and definitions for integrated analyses by all the interfacing parties. Any payload interfaces that are out of scope with the standard interfaces defined shall be defined in a Payload Unique Interface Control Document (ICD) for a given payload. Each Payload Unique ICD will have comparable paragraphs to this ICD and will have a corresponding notation of A, for applicable; N/A, for not applicable; N, for note added for explanation; and E, for exception. On any flight, the STS reserves the right to assign locations to both payloads mounted on an adapter plate(s) and payloads stored within standard lockers. Specific locations requests and/or requirements exceeding standard mid-deck payload requirements may result in a reduction in manifesting opportunities.

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NASA NTRS1987

A systems-level performance history of get away specials after 25 Space Shuttle missions

This paper summarizes the results of a thorough performance study of Get Away Special (GAS) payloads that was conducted in 1986. During the study a complete list of standard and nonstandard GAS payloads vs. Shuttle mission was constructed, including specific titles for the experiments in each canister. A broad data base for each canister and each experiment was then compiled. Performance results were then obtained for all but a few experiments. The canisters and experiments were subsequently categorized according to the degree of experiment success. For those experiments that experienced failures or anomalies, several correlations and generalizations were extracted from individual subsystem performance data. Recommendations are made which may enhance the success and performance of future GAS payloads.

Ridenoure, Rex W.↗
NASA NTRS2007

Enhancing the NASA Expendable Launch Vehicle Payload Safety Review Process Through Program Activities

The safety review process for NASA spacecraft flown on Expendable Launch Vehicles (ELVs) has been guided by NASA-STD 8719.8, Expendable Launch Vehicle Payload Safety Review Process Standard. The standard focused primarily on the safety approval required to begin pre-launch processing at the launch site. Subsequent changes in the contractual, technical, and operational aspects of payload processing, combined with lessons-learned supported a need for the reassessment of the standard. This has resulted in the formation of a NASA ELV Payload Safety Program. This program has been working to address the programmatic issues that will enhance and supplement the existing process, while continuing to ensure the safety of ELV payload activities.

Palo, Thomas E.↗
NASA NTRS1975

Evaluation philosophy for shuttle launched payloads

Some approaches to space-shuttle payload evaluation are examined. Issues considered include subsystem replacement in low-cost modular spacecraft (LCMS), validation of spacelab payloads, the use of standard components in shuttle-era spacecraft, effects of shuttle-induced environments on payloads, and crew safety. The LCMS is described, and goals are discussed for its evaluation program. Concepts regarding how the evaluation should proceed are considered.

Heuser, R. E.↗
NASA NTRS1991

ELV payload environment; Proceedings of the NASA-Industry Conference on Launch Environments of ELV Payloads, Elkridge, MD, June 4-6, 1990

Various papers on the ELV payload environment are presented. Individual topics addressed include: EnviroNET: the Space Environment Information Service, ELV Payload Environments Study, perspective of GSFC Orbital Launch Services Office, Cosmic Background Explorer, the Standard Booster Interface, MLV Standard Interface Study, future payload requirements, General Dynamics Atlas family, Delta II Launch Vehicle environments, Titan vibroacoustics, Titan IV, the Scout Launch Vehicle, Pegasus.

Lauriente, Michael↗
NASA NTRS2010

Streamlining Payload Integration

Payload integration onto space transport vehicles and the International Space Station (ISS) is a complex process. Yet, cargo transport is the sole reason for any space mission, be it for ferrying humans, science, or hardware. As the largest such effort in history, the ISS offers a wide variety of payload experience. However, for any payload to reach the Space Station under the current process, Payload Developers face a list of daunting tasks that go well beyond just designing the payload to the constraints of the transport vehicle and its stowage topology. Payload customers are required to prove their payload s functionality, structural integrity, and safe integration - including under less than nominal situations. They must also plan for or provide training, procedures, hardware labeling, ground support, and communications. In addition, they must deal with negotiating shared consumables, integrating software, obtaining video, and coordinating the return of data and hardware. All the while, they must meet export laws, launch schedules, budget limits, and the consensus of more than 12 panel and board reviews. Despite the cost and infrastructure overhead, payload proposals have increased. Just in the span from FY08 to FY09, the NASA Payload Space Station Support Office budget rose from $78M to $96M in attempt to manage the growing manifest, but the potential number of payloads still exceeds available Payload Integration Management manpower. The growth has also increased management difficulties due to the fact that payloads are more frequently added to a flight schedule late in the flow. The current standard ISS template for payload integration from concept to payload turn-over is 36 months, or 18 months if the payload already has a preliminary design. Customers are increasingly requiring a turn-around of 3 to 6-months to meet market needs. The following paper suggests options for streamlining the current payload integration process in order to meet customer schedule needs and reduce costs for both the integration support teams and the developers, without reducing quality or compromising safety. Issues for the key integration areas of planning, training, verification, and safety are presented in a Root-Cause Analysis study, with plausible solutions provided that involve technology and tools already available to the ISS community. Although based upon the ISS process, the payload integration techniques outlined herein also offer an integration template for any space transport endeavor.

Lufkin, Susan N.↗
NASA NTRS2004

A High-Energy Technology Demonstration Platform: The First Step in a Stepping Stones Approach to Energy-Rich Space Infrastructures

The slide presentation examines advanced technologies in spacecraft design, space solar power primary payload options, modular spacecraft design, and spacecraft compatible with medium ELV performance. The discussion of advanced technologies in spacecraft design includes power subsystem sized to satisfy all near-term spacecraft power needs, spacecraft bus provides test-bed for maturing technologies, and no insurmountable technical hurdles. The discussion of space solar power primary payload options examines large envelope with standard interfaces reserved for high-power payload. The discussion of modular spacecraft design includes upgrade opportunities, capability for mission tailoring, and bus qualified for most launch vehicles. This discussion of spacecraft compatible with medium ELV performance includes mass capability to ISS orbit and fairing capability for large payloads on the bus.

Carrington, Connie↗
NASA NTRS1988

Future MAUS payload and the TWIN-MAUS configuration

The German MAUS project (materials science autonomous experiments in weightlessness) was initiated in 1979 for optimum utilization of NASA's Get Away Special (GAS) program. The standard MAUS system was developed to meet GAS requirements and can accommodate a wide variety of GAS-type experiments. The system offers a range of services to experimenters within the framework of standardized interfaces. Four MAUS payloads being prepared for future space shuttle flight opportunities are described. The experiments include critical Marangoni convection, oscillatory Marangoni convection, pool boiling, and gas bubbles in glass melts. Scientific objectives as well as equipment hardware are presented together with recent improvements to the MAUS standard system, e.g., a new experiment control and data management unit and a semiconductor memory. A promising means of increasing resources in the field of GAS experiments is the interconnection of GAS containers. This important feature has been studied to meet the challenge of future advanced payloads. In the TWIN-MAUS configuration, electrical power and data will be transferred between two containers mounted adjacent to each other.

Staniek, S.↗