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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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NASA NTRS1972

The Skylab orbital laboratory.

The Skylab orbital laboratory is described in terms of spacecraft design features, the experiment programs, and the schedule of planned missions. Attention is given to flight and crew operations, rescue measures, the Multiple Docking Adapter, the Airlock Module, the Workshop, the Apollo Telescope Mount, Saturn V booster, Command and Service Modules, the life support system, thermal and environmental control, electrical power, attitude and pointing control, instrumentation and communications, crew equipment, provisions, and stowage.

Schneider, W. C.↗

NASA NTRS2001

STS-97 Post Flight Presentation

Various shots highlight the STS-97 Endeavour mission. Footage shows the crew suiting up and leaving the Operations and Checkout (O&C) Building, the launch, and landing. Various on-orbit activities are seen, such as docking with the International Space Station (ISS), the spacewalks (installing the PV Module P6), array deployment, meeting the Expedition 1 crew, eating, and undocking. Shots show the northern lights and a meteorite entering Earth's atmosphere from above. The Andes can be seen from the Orbiter while the P6 arrays are deploying.

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NASA NTRS2001

STS-100 Photo-op/Shut-up/Depart O&C/Launch Endeavour On Orbit/Landing/Crew Egress

This video shows an overview of crew activities from STS-100. The crew of Space Shuttle Shuttle Endeavour includes: Commander Kent Rominger; Pilot Jeffrey Ashby; and Mission Specialists Chris Hadfield, John Phillips, Scott Parazynski, Umberto Guidoni, and Yuri Lonchakov. Sections of the video include: Photo-op; Suit-up; Depart O&C; Ingress; Launch with Playbacks; On-orbit; Landing with Playbacks; Crew Egress & Departure. Voiceover narration introduces the astronauts at their pre-flight meal, and continues during the video, except for the launch and landing sequences. Launch playback views include: NEXT; Beach Tracker; VAB; PAD-A; Tower-1; UCS-15; Grandstand; OTV-60; OTV-70; OTV-71; DOAMS; UCS-10 Tracker; UCS-23 Tracker; On-board Ascent Camera. The On-orbit section of the video shows preparations for an extravehicular activity (EVA) to install Canadarm 2 on the International Space Station (ISS). Preparation for docking with the ISS, and the docking of the orbiter and ISS are shown. The attachment of Canadarm 2 and the Raffaello Logistics Module, a resupply vehicle, are shown. The crew also undertakes some maintenance of the ISS. Landing playback views include: TV-1; TV-2; LRO-1; LRO-2; PPOV.

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NASA NTRS2015

Preparing for Mars: The Evolvable Mars Campaign 'Proving Ground' Approach

As the National Aeronautics and Space Administration (NASA) prepares to extend human presence beyond Low Earth Orbit, we are in the early stages of planning missions within the framework of an Evolvable Mars Campaign. Initial missions would be conducted in near-Earth cis-lunar space and would eventually culminate in extended duration crewed missions on the surface of Mars. To enable such exploration missions, critical technologies and capabilities must be identified, developed, and tested. NASA has followed a principled approach to identify critical capabilities and a "Proving Ground" approach is emerging to address testing needs. The Proving Ground is a period subsequent to current International Space Station activities wherein exploration-enabling capabilities and technologies are developed and the foundation is laid for sustained human presence in space. The Proving Ground domain essentially includes missions beyond Low Earth Orbit that will provide increasing mission capability while reducing technical risks. Proving Ground missions also provide valuable experience with deep space operations and support the transition from "Earth-dependence" to "Earth-independence" required for sustainable space exploration. A Technology Development Assessment Team identified a suite of critical technologies needed to support the cadence of exploration missions. Discussions among mission planners, vehicle developers, subject-matter-experts, and technologists were used to identify a minimum but sufficient set of required technologies and capabilities. Within System Maturation Teams, known challenges were identified and expressed as specific performance gaps in critical capabilities, which were then refined and activities required to close these critical gaps were identified. Analysis was performed to identify test and demonstration opportunities for critical technical capabilities across the Proving Ground spectrum of missions. This suite of critical capabilities is expected to provide the foundation required to enable a variety of possible destinations and missions consistent with the Evolvable Mars Campaign.. The International Space Station will be used to the greatest extent possible for exploration capability and technology development. Beyond this, NASA is evaluating a number of options for Proving Ground missions. An "Asteroid Redirect Mission" will demonstrate needed capabilities (e.g., Solar Electric Propulsion) and transportation systems for the crew (i.e., Space Launch System and Orion) and for cargo (i.e., Asteroid Redirect Vehicle). The Mars 2020 mission and follow-on robotic precursor missions will gather Mars surface environment information and will mature technologies. NASA is considering emplacing a small pressurized module in cis-lunar space to support crewed operations of increasing duration and to serve as a platform for critical exploration capabilities testing (e.g., radiation mitigation; extended duration deep space habitation). In addition, "opportunistic mission operations" could demonstrate capabilities not on the Mars critical path that may, nonetheless, enhance exploration operations (e.g., teleoperations, crew assisted Mars sample return). The Proving Ground may also include "pathfinder" missions to test and demonstrate specific capabilities at Mars (e.g., entry, descent, and landing). This paper describes the (1) process used to conduct an architecture-driven technology development assessment, (2) exploration mission critical and supporting capabilities, and (3) approach for addressing test and demonstration opportunities encompassing the spectrum of flight elements and destinations consistent with the Evolvable Mars Campaign.

Bobskill, Marianne R.↗

NASA NTRS2020

Lunar Transient Accelerations White Paper

Recently, the United States announced a plan to return astronauts to the moon by 2024 [8]. Lunar landing (and subsequent Mars landing) architecture was not considered when the current NASA standards and vehicle design requirements for crew injury risk were developed. Therefore a gap exists in protecting the crew in planetary landing scenarios. One of the interesting aspects of this design reference mission (DRM)is the consideration of having the crew stand during dynamic phases of flight. Although this approach was contemplated for the Apollo Lunar Module, current NASA standards do not address design solutions that allow the crew to stand. Currently, NASA uses several tools and associated limits to mitigate crew injury because of dynamic loads. Some of these tools are the Brinkley Dynamic Response Criterion (BDRC) model and Hybrid III Anthropomorphic Test Devices (ATDs) [10]; and these have several limitations for assessing spaceflight loading environments, as well as specific underlying assumptions that may not be applicable in planetary landing vehicles. The BDRC is a simple lumped mass parameter model developed by the U.S. military, and has been used primarily to evaluate injury risk associated with aircraft ejection systems. The model evaluates seat accelerations in each axis to determine injury risk. Because the model treats the human-seat-restraint system as a single system, it is contingent on a restraint system and seat with similar characteristics of the original test data underlying the model. In particular, the model requires a rigid seat with a minimum natural frequency of 15Hz, minimal seat pan padding, side supports, and multipoint harness. The BDRC model uses undamped natural frequency and damping coefficients based on these requirements and any deviations may render the model injury predictions void. In lunar landing, one expects that a minimal or even no seat with minimal restraints will be employed. In this case, the original model parameters are likely to not be applicable. For capsule-based spacecraft returning crew to Earth, the Hybrid III ATD in various sizes also is used to supplement the BDRC. This analytical tool was added to address limitations in the BDRC related to spacecraft landings while wearing a pressure garment and helmet. Although the Hybrid III ATD has additional measurement capability; head, neck,and lumbar spine responses were the only metrics included because of the limitations imposed by the model.Lunar landing acceleration limits must assume the crew is standing during landing, an orientation for which we have limited data.Although the Apollo missions did employ a standing orientation for the crew, much of the data is lost. Therefore data from othersources havebeen examined to inform lunar landing acceleration limits.

Jeffrey T Somers↗

NASA NTRS1996

STS-79 Flight Day 3

On this third day of the STS-79 mission, the flight crew, Cmdr. William F. Readdy, Pilot Terrence W. Wilcutt, Mission Specialists, Thomas D. Akers, John E. Blaha, Jay Apt, and Carl E. Walz, start another busy day on orbit activating experiments in the Spacehab module. Readdy and Wilcutt are seen conducting two rendezvous burns while other crew members are seen working in the Spacehab module. The Active Rack Isolation System, or ARIS, is tended to by Walz, who performs a minor maintenance procedure on one of ARIS' vibration-damping pushrods while Akers works with an inventory management system using a bar code reader to more effectively keep track of items that will be transferred back and forth between the Shuttle and the Mir. Apt continues work with a furnace which heats to nearly 1,600 degrees centigrade to melt metal samples for study after the flight. Apt also provides a television tour of the Spacehab, which is twice its normal size for this flight to allow extra room for science experiments and logistical items slated for transfer to Mir.

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NASA NTRS2001

STS-102/Expedition 2 Mission Overview

John Shannon, STS-102 Lead Flight Director, Bernestine Dickey, STS-102 Launch Package Manager, and Rick La Brode, International Space Station (ISS) Lead Flight Director, give an overview of the STS-102 mission during a prelaunch press conference. Mr. Shannon discusses how the mission came into being and its objectives, including information on the launch and a day-by-day account of mission activities. Ms. Dickey gives details on the payload of STS-102, describing the system racks, cargo elements, and crew supplies delivered via the Leonardo Multi-Purpose Logistics Module. Mr. La Brode describes the current configuration of the ISS and upcoming changes. He also discusses the activities of the Expedition 2 crew during the next four months. Computer simulations show the ISS' current and future (after the STS-102 mission) configurations, the installations of Leonardo, and the move of the Pressurized Mating Adapter from one port to another on the Destiny Laboratory. The panel then answers questions from the press.

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NASA NTRS1973

Mission requirements: Skylab rescue mission SL-R

The Skylab Program includes three low earth orbit missions. These missions are designated SL-1/SL-2,SL-3 and SL-4. In addition to the three nominal Skylab missions, the program includes the Skylab Rescue Mission (SL-R). The SL-R mission is designed to provide a safe return of the Skylab crew in the event the Command Service Module (CSM) becomes disabled while docked to the Saturn Workshop (SWS). Mission requirements for the SL-R mission only are presented. SL-R mission configuration will be a CSM (modified with a field installed kit) manned by two crewmen launched on a Saturn IB Launch Vechicle. The SL-R CSM will rendezvous and dock with the SWS (or Orbital Assembly (OA), consisting of the SWS and disabled CSM, if the disabled CSM has not previously been jettisoned). The SWS configuration includes a Multiple Docking Adapter (MDA), Apollo Telescope Mount (ATM), Airlock Module (AM), and an S-IVB stage (modified as an Orbital Workshop (OWS), previously launched and inserted into orbit on a two-stage Saturn V Launch Vehicle for the SL-1/SL-2 mission.

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NASA NTRS1975

Apollo Program Summary Report: Synopsis of the Apollo Program Activities and Technology for Lunar Exploration

Overall program activities and the technology developed to accomplish lunar exploration are discussed. A summary of the flights conducted over an 11-year period is presented along with specific aspects of the overall program, including lunar science, vehicle development and performance, lunar module development program, spacecraft development testing, flight crew summary, mission operations, biomedical data, spacecraft manufacturing and testing, launch site facilities, equipment, and prelaunch operations, and the lunar receiving laboratory. Appendixes provide data on each of the Apollo missions, mission type designations, spacecraft weights, records achieved by Apollo crewmen, vehicle histories, and a listing of anomalous hardware conditions noted during each flight beginning with Apollo 4.

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NASA NTRS1989

What's on Freedom for users?

The design and use of the Space Station Freedom are discussed. The contributions to the Station from EAS, Japan, Canada, and the US are described. Consideration is given to the capability of the Station, the internal accommodations for crew and payloads, various applications for the modules, and the planning and operation of the payloads.

Williams, Richard J.↗

NASA NTRS1993

Soyuz-TM-based interim Assured Crew Return Vehicle (ACRV) for the Space Station Freedom

The concept of using the available Soyuz-TM Assured Crew Return Vehicle (ACRV) spacecraft for the assurance of the safety of the Space Station Freedom (SSF) crew after the departure of the Space Shuttle from SSF was proposed by the NPO Energia and was accepted by NASA in 1992. The ACRV will provide the crew with the capability to evacuate a seriously injured/ill crewmember from the SSF to a ground-based care facility under medically tolerable conditions and with the capability for a safe evacuation from SSF in the events SSF becomes uninhabitable or the Space Shuttle flights are interrupted for a time that exceeds SSF ability for crew support and/or safe operations. This paper presents the main results of studies on Phase A (including studies on the service life of ACRV; spacecraft design and operations; prelaunch processing; mission support; safety, reliability, maintenance and quality and assurance; landing, and search/rescue operations; interfaces with the SSF and with Space Shuttle; crew accommodation; motion of orbital an service modules; and ACRV injection by the Expendable Launch Vehicles), along with the objectives of further work on the Phase B.

Yu P Semenov↗

NASA NTRS2000

STS-101 Mission Highlights Resource Tape, Part 2 of 3

A continuation of 'STS-101 Mission Highlights Resource Tape, Part 1 of 3', footage shows the activities of flight days five through ten. The crew of STS-101 (Commander James D. Halsell, Jr. and Mission Specialists Mary Ellen Weber, Jeffrey N. Williams, James S. Voss, Susan J. Helms, and Yuri Vladimirovich Usachev) are seen during ingress between the Atlantis Orbiter and the International Space Station (ISS) and as they transfer equipment from Atlantis to the ISS. The crew is shown working in the Zarya module and leaving ISS just before resealing the connecting hatches. Footage shows the successful undocking of Atlantis. The activities of flight day 11 and landing can be seen on 'STS-101 Mission Highlights Resource Tape, Part 3 of 3'.

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NASA NTRS2001

STS-105 Flight Day 3 Highlights

On this third day of the STS-105 mission, footage shows Discovery docking with the International Space Station (ISS). The Expedition 2 crewmembers, Yuriy Usachev, James Voss, and Susan Helms, are seen as they work in the Destiny Laboratory Module on the ISS. The STS-105 crew (Commander Scott Horowitz, Pilot Frederick Sturckow, and Mission Specialists Daniel Barry and Patrick Forrester), Expedition 2 crew, and Expedition 3 crew (Frank Culbertson, Jr., Mikhail Turin, and Vladimir Dezhurov) are seen as the connecting hatches are opened between the ISS and Discovery and the crews meet.

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NASA NTRS2002

STS-108 Mission Highlights Resource Tape

This video is a continuation of 'STS-108 Mission Highlights Resource Tape: Part 1 of 3' (Internal ID 2002049331). Flight day four footage continues with a video tour of the International Space Station (ISS). During flight day five, an exterior view of the Multipurpose Logistics Module (MPLM) is seen, followed by the crew unloading the supplies and equipment from the MPLM. Commander Dominic Gorie and Mission Specialist Linda Godwin are seen making preparations for the Extravehicular Activity (EVA) scheduled for the following day. Footage of an exterior view of the ISS is also shown. Flight day six footage includes Godwin and Mission Specialist Daniel Tani suiting up for their EVA and the installation of thermal blankets around the solar array wings of the ISS. Expedition 3 Commander Frank Culbertson is seen working in the ISS laboratory during flight day seven. Views are shown of Saudi Arabia and the Red Sea, the western coast of Australia, Cuba and Florida, and Switzerland and Northern Italy. During flight day eight, the crew is seen stowing objects in the MPLM for return to earth. The video concludes with footage of the treadmill used by the astronauts for physical exercise. Flight days nine through twelve are included in 'STS-108 Mission Highlights Resource Tape: Part 3 of 3' (Internal ID 2002049329).

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NASA NTRS2008

Enabling and Enhancing Space Mission Success and Reduction of Risk through the Application of an Integrated Data Architecture

The engineering phases of design, development, test, and evaluation (DDT and E) and subsequent planning, preparation, and operation (Ops) of space vehicles in a complex and distributed environment requires massive and continuous flows of information across the enterprise and across temporal stages of the vehicle lifecycle. The resulting capabilities at each subsequent stage depend in part on the capture, preparation, storage, and subsequent provision of information from prior stages. The United States National Aeronautics and Space Administration (NASA) is currently designing a fleet of new vehicles that will replace the Space Shuttle and expand space operations and exploration capabilities. This includes the 2 stage human rated lift vehicle Ares 1 and its associated crew vehicle the Orion, and a service module; the heavy lift cargo vehicle, Ares 5, and an associated cargo stage known as the Earth Departure Stage; and a Lunar Lander vehicle that contains a descent stage, and ascent stage, and a habitation module. A variety of concurrent assorted ground operations infrastructure including software and facilities are also being developed, assorted technology and assembly designs and development for equipment such as EVA suits, life support systems, command and control technologies are also in the pipeline. The development is occurring in a distributed manner, with project deliverables being contributed by a large and diverse assortment of vendors and most space faring nations. Critical information about all of the components, software, and procedures must be shared during the DDT and E phases and then made readily available to the mission operations staff for access during the planning, preparation, and operations phases, and also need to be readily available for system to system interactions. The Constellation Data Systems Project (CxDS) is identifying the needs, and designing and deploying systems and processes to support these needs. This paper details the steps and processes that NASA is applying within the Constellation Program to manage this data and information, and to insure that the correct information is available, correctly annotated, and can be provisioned digitally to enhance response times, and support engineering analysis and anomaly resolution.

Brummett, Robert C.↗

NASA NTRS2012

A Study for Mars Manned Exploration

Over the last five decades there have been numerous studies devoted to developing, launching and conducting a manned mission to Mars by both Russian and U.S. organizations. These studies have proposed various crew sizes, mission length, propulsion systems, habitation modules, and scientific goals. As a first step towards establishing an international partnership approach to a Mars mission, the most recent Russian concepts are explored and then compared to NASA's latest Mars reference mission.

Dorney, Daniel J.↗

NASA NTRS2012

Possible Scenarios for Mars Manned Exploration

Dorney, Daniel J.↗

NASA NTRS2017

Overview of the Acoustic Testing of the European Service Module Structural Test Article (E-STA)

The European Space Agency (ESA) and their prime contractor Airbus Defense Space (ADS) are developing the European Service Module (ESM) for integration and utilization with other modules of NASAs Orion Multi-Purpose Crew Vehicle. As part of this development, ESA, ADS, NASA and the Lockheed Martin Company performed a series of reverberant acoustic tests in April-May 2016 on the ESM Structural Test Article (E-STA), the mechanical mock-up of the ESM designated for mechanical tests. Testing the E-STA under acoustic qualification loads verifies whether it can successfully withstand the medium and high frequency mechanical environment occurring during the vehicles lift-off and atmospheric phases of flight. The testing occurred at the Reverberant Acoustic Test Facility (RATF) at the NASA Glenn Research Centers Plum Brook Station site in Sandusky, OH, USA. This highly successful acoustic test campaign excited the E-STA to acoustic test levels as high as 149.4 dB Overall Sound Pressure Level. This acoustic testing met all the ESA and ADSs test objectives, including establishing/verifying the random vibration qualification test levels for numerous hardware components of the ESM, and qualifying the ESMs Solar Array Wing electrical power system. This paper will address the test objectives, the test articles configuration, the test instrumentation and excitation levels, the RATF site and capabilities, the series of acoustic tests performed, and the technical issues faced and overcome to result in a successful acoustic test campaign for the ESM. A discussion of several test results is also included.

Qualification↗