Search NASA⌕ Search

SEARCH · Search NASA

Results for “Science Missions”

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.

Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.

At least 127 records · Page 7
All sourcesNASA NTRSDOE OSTI
NASA NTRS2009

Potential Astrophysics Science Missions Enabled by NASA's Planned Ares V

NASA s planned Ares V cargo vehicle with its 10 meter diameter fairing and ~60,000 kg payload mass to L2 offers the potential to launch entirely new classes of space science missions such as 8-meter monolithic aperture telescopes, 12- meter aperture x-ray telescopes, 16 to 24 meter segmented telescopes and highly capable outer planet missions. The paper will summarize the current Ares V baseline performance capabilities and review potential mission concepts enabled by these capabilities.

Stahl, H. Philip↗
NASA NTRS1995

Robotic Planetary Science Missions Enabled with Small NTR Engine/Stage Technologies

The high specific impulse (Isp) and engine thrust-to-weight ratio of liquid hydrogen (LH2)-cooled nuclear thermal rocket (NTR) engines makes them ideal for upper stage applications to difficult robotic planetary science missions. A small 15 thousand pound force (klbf) NTR engine using a uranium-zirconium-niobium 'ternary carbide' fuel (Isp approximately 960 seconds at approximately 3025K) developed in the Commonwealth of Independent States (CIS) is examined and its use on an expendable injection stage is shown to provide major increases in payload delivered to the outer planets (Saturn, Uranus, Neptune and Pluto). Using a single 'Titan IV-class' launch vehicle, with a lift capability to low Earth orbit (LEO) of approximately 20 metric tons (t), an expendable NTR upper stage can inject two Pluto 'Fast Flyby' spacecraft (PFF/SC) plus support equipment-combined mass of approximately 508 kg--on high energy, '6.5-9.2 year' direct trajectory missions to Pluto. A conventional chemical propulsion mission would use a liquid oxygen (LOX)/LH2 'Centaur' upper stage and two solid rocket 'kick motors' to inject a single PFF/SC on the same Titan IV launch vehicle. For follow on Pluto missions, the NTR injection stage would utilize a Jupiter 'gravity assist' (JGA) maneuver to launch a LOX/liquid methane (CH4) capture stage (Isp approximately 375 seconds) and a Pluto 'orbiter' spacecraft weighing between approximately 167-312 kg. With chemical propulsion, a Pluto orbiter mission is not a viable option because c inadequate delivered mass. Using a 'standardized' NTR injection stage and the same single Titan IV launch scenario, 'direct flight' (no gravity assist) orbiter missions to Saturn, Uranus and Neptune are also enabled with transit times of 2.3, 6.6, and 12.6 years, respectively. Injected mass includes a storable, nitrogen tetroxide/monomethyl hydrazine (N2O4/MMH) capture stage (Isp approximately 330 seconds) and orbiter payloads 340 to 820% larger than that achievable using a LOX/LH2-fueled injection stage. The paper discusses NTR technology and mission characteristics, shows NTR stage and payload accommodations within the 26.2 m long Titan IV payload fairing, and discusses NTR stage performance as a function of assumed cryogenic tank technology.

Borowski, Stanley K.↗
NASA NTRSDate not supplied

Enabling New and Innovative Low Cost Mars Science Missions with the Adaptable, Deployable, Entry and Placement Technology (ADEPT)

The Adaptive Deployable Entry and Placement Technology (ADEPT) offers a delivery capability for Small Sat or CubeSat orbiter(s), in-situ elements, or landers. ADEPT can deliver the same science payload to a destination with a stowed diameter a factor of 3-4 times smaller than an equivalent rigid aeroshell, alleviating volumetric constraints on the secondary payload accommodation or primary carrier spacecraft bus. The ADEPT system can support payload over a range of mass and geometries to offer a delivery capability for a single or constellation of spacecraft supporting the goals and objectives of “Low Cost Mars Science Missions.”

ADEPT↗
NASA NTRS2019

New Observing Strategy (NOS) for Future Earth Science Missions

One of the new thrusts of the Earth Science Technology Office (ESTO) Advanced Information Systems Technology (AIST) Program is the New Observing Strategy (NOS) thrust. Its goal is to provide a framework for identifying technology advances needed to exploit newly available observational capabilities, particularly to enable the development of the information technologies needed to support planning, evaluating, implementing, and operating dynamic, multi-element sets of observing assets. In this paper, we will introduce relevant NOS terminology and some key concepts before describing the objectives, driving factors and technology goals of this new thrust.

Advanced Information Systems↗
NASA NTRS2012

Benefits of Delay Tolerant Networking for Earth Science Missions

To date there has been much discussion about the value of Delay Tolerant Networking (DTN) for space missions. Claims of various benefits, based on paper analysis, are good; however a benefits statement with empirical evidence to support is even better. This paper presents potential and actual advantages of using DTN for Earth science missions based on results from multiple demonstrations, conducted by the Communications, Standards, and Technology Laboratory (CSTL) at NASA Goddard Space Flight Center (GSFC). Demonstrations included two flight demonstrations using the Earth Observing Mission 1 (EO-1) and the Near Earth Network (NEN), a ground based demonstration over satellite links to the Internet Router in Space (IRIS) payload on Intelsat-14, and others using the NASA Tracking Data Relay Satellite System (TDRSS). Real and potential findings include increased flexibility and efficiency in science campaigns, reduced latency in a collaborative science scenario, and improved scientist-instrument communication and control.

Davis, Faith↗
NASA NTRSDate not supplied

Nuclear Electric Propulsion for Outer Planet Science Missions

Nuclear electric propulsion (NEP) combines the high specific impulse of electric thrusters with a constant power source that can operate anywhere in the solar system. Current investments in fission surface power offer a starting point for development of an NEP capability for deep space science missions, with a mission to the Saturn system illustrating the potential of such a system. Minimum time of flight transits, maximum payload delivery, and a sample return from Enceladus are considered. The NEP system can deliver payloads to the Saturn system with similar transit times to the Cassini spacecraft without requiring the planetary flyby maneuvers, and when coupled with a heavy-lift launch vehicle an NEP-powered spacecraft can complete a Saturn transit significantly faster than Cassini. High payload masses can be delivered on a longer trajectory at the expense of transit time. Replacing a portion of the payload with propellant allows for a high degree of maneuverability upon reaching the Saturn system. An Enceladus sample return mission closes when utilizing the NEP system for the Saturn departure and Earth return burns.

Matthew E Duchek↗
NASA NTRS2011

A Small Fission Power System with Stirling Power Conversion for NASA Science Missions

In early 2010, a joint National Aeronautics and Space Administration (NASA) and Department of Energy (DOE) study team developed a concept for a 1 kWe Fission Power System with a 15-year design life that could be available for a 2020 launch to support future NASA science missions. The baseline concept included a solid block uranium-molybdenum reactor core with embedded heat pipes and distributed thermoelectric converters directly coupled to aluminum radiator fins. A short follow-on study was conducted at NASA Glenn Research Center (GRC) to evaluate an alternative power conversion approach. The GRC study considered the use of free-piston Stirling power conversion as a substitution to the thermoelectric converters. The resulting concept enables a power increase to 3 kWe with the same reactor design and scalability to 10 kW without changing the reactor technology. This paper presents the configuration layout, system performance, mass summary, and heat transfer analysis resulting from the study.

Mason, Lee↗
NASA NTRS1995

The influence of space flight on erythrokinetics in man. Space Life Sciences Missions 1 and 2. Experiment E261

The purpose of this contract was to design and conduct experiments that would increase our understanding of the influence of space flight on erythrokinetics and the rapid change that occurs in the red blood cell mass during spaceflight. The experiment designated E261, was flown on Space Life Science missions SLS-1 and SLS-2 (STS 40 and STS 58). Unique features of this experiment included radionuclide tracer studies during flight and frequent in-flight blood samples specifically for the first three or four days of the mission. Plasma volume measurements were made early and late in the missions. Radioactive iron kinetics studies were initiated after one or three days in microgravity since the magnitude of the red blood cell mass decrease dictated that bone marrow production must be decreased very early in the flight. The schedule was designed to study the time course of the changes that occur during spaceflight and to possibly define a mechanism for the rapid reduction in red blood cell mass.

Alfrey, Clarence P.↗
NASA NTRS2004

Development of Solar Sail Propulsion for Inner Solar System NASA Science Missions

This paper examines recent assessments of the technology challenges facing solar sails, identifies the systems and technologies needing development, and the approach employed by NASA's In-Space Propulsion program in NASA to achieve near-term products that move this important technology from low technology readiness level toward the goal of application to science missions in near-Earth space and beyond.

Montgomery, Edward E., IV↗
NASA NTRS2004

The Development of Solar Sail Propulsion for NASA Science Missions to the Inner Solar System

This paper examines recent assessments of the technology challenges facing solar sails, identifies the systems and technologies needing development, and the approach employed by NASA's In-space Propulsion Program in NASA to achieve near term products that move this important technology from low technology readiness level (TRL) toward the goal of application to science missions in near earth space and beyond. The status of on-going efforts to design, build, and test ground demonstrators of alternate approaches to structures (inflatable versus rigid), membrane materials, optical shape sensing, and attitude control will be presented along with planned future investments.

Montgomery, Edward E, IV↗
NASA NTRS2020

Cryogenic Hydrogen Oxygen Propulsion System for Planetary Science Missions

A Cryogenic Hydrogen Oxygen Propulsion System (CHOPS) that uses liquid hydrogen (LH2) and liquid oxygen (LO2) propellants can dramatically enhance NASA's ability to explore the solar system due to their superior specific impulse (Isp) capability. Although these cryogenic propellants can be challenging to manage and store, they allow significant mass advantages over traditional hypergolic propulsion systems and are therefore enabling for many planetary science missions. New cryogenic storage techniques such as subcooling, advanced insulation, low thermal conductivity structures allow for the long term storage and use of cryogenic propellants for solar system exploration and hence allow NASA to deliver more payloads to targets of interest, launch on smaller and less expensive launch vehicles, or both.

Mustafi, Shouvanik↗
NASA NTRS2006

Rapid Development of Gossamer Propulsion for NASA Inner Solar System Science Missions

Over a two and one-half year period dating from 2003 through 2005, NASA s In-Space Propulsion Program matured solar sail technology from laboratory components to full systems, demonstrated in as relevant a space environment as could feasibly be simulated on the ground. This paper describes the challenges identified; as well as the approaches taken toward solving a broad set of issues spanning material science, manufacturing technology, and interplanetary trajectory optimization. Revolutionary advances in system structural predictive analysis and characterization testing occurred. Also addressed are the remaining technology challenges that might be resolved with further ground technology research, geared toward reducing technical risks associated with future space validation and science missions.

Young, Roy M.↗
NASA NTRSDate not supplied

NASA’s Space Launch System: High C3 Launch Capability for Science Missions

As NASA’s initial Space Launch System (SLS) Block 1 vehicle enters integration and stacking operations at Kennedy Space Center (KSC) this year in preparation for a 2021 launch, work is in progress on future more powerful variants of the vehicle. Available in the mid 2020s and 2030s, Block 1B and Block 2 will feature increased performance and unparalleled volume for payloads, providing an enabling launch option for science mission planners. The baseline SLS architecture consists of two five-segment solid rocket boosters and four RS-25 LH2/LOX engines. The evolved Block 1B and Block 2 vehicles use a four-engine LH2/LOX upper stage and can be outfitted with an 8.4 m-diameter pay-load fairing. Additional upper stages can be packaged in the 8.4 m fairing to enable high C3 (in the range of 300 km2/sec2) missions to Mercury, the Jovian system, the ice giants, the Kuiper Belt and beyond.

Stephen D Creech↗
NASA NTRS2016

Advances in Starshade Technology Readiness for an Exoplanet Characterizing Science Mission in the 2020's

The discovery of thousands of exoplanets is generating increasing interest in the direct imaging and characterization of these planets. Starshade, and eternal occulter, could fly in formation between a telescope and distant star, blocking out the light from the star, and enabling us to focus on the light of any orbiting planets. Recent technology developments in coordination with system design, has added much needed detail to define the technology requirements for a science mission that could launch in the 2020's. This paper address the mechanical architecture, the successful efforts to date, the current state of design for the mechanical system, and upcoming technology efforts.

occulter↗
NASA NTRS2010

Identification and Classification of Common Risks in Space Science Missions

Due to the highly constrained schedules and budgets that NASA missions must contend with, the identification and management of cost, schedule and risks in the earliest stages of the lifecycle is critical. At the Jet Propulsion Laboratory (JPL) it is the concurrent engineering teams that first address these items in a systematic manner. Foremost of these concurrent engineering teams is Team X. Started in 1995, Team X has carried out over 1000 studies, dramatically reducing the time and cost involved, and has been the model for other concurrent engineering teams both within NASA and throughout the larger aerospace community. The ability to do integrated risk identification and assessment was first introduced into Team X in 2001. Since that time the mission risks identified in each study have been kept in a database. In this paper we will describe how the Team X risk process is evolving highlighting the strengths and weaknesses of the different approaches. The paper will especially focus on the identification and classification of common risks that have arisen during Team X studies of space based science missions.

Risk Identification↗
NASA NTRSDate not supplied

Small Satellite-sized Hypersonic Inflatable Decelerators for Interplanetary Science Missions

To take full advantage of our increased access to space, through reduced launch costs that ridesharing opportunities present, innovative and lower cost options for interplanetary exploration are needed. Capitalizing on the technology miniaturization trends and the SmallSat class of vehicles could provide advancements for interplanetary space exploration. Presented here, are the results of a feasibility study conducted during an internship at NASA Langley Research Center that explored the use of a SmallSat-sized Hypersonic Inflatable Aerodynamic Decelerator (HIAD) to enable interplanetary orbital science missions via aerocapture.

Shelly C. Mann↗
NASA NTRSDate not supplied

Small Satellite-sized Hypersonic Inflatable Decelerators for Interplanetary Science Missions

To take full advantage of our increased access to space, through reduced launch costs that ridesharing opportunities present, innovative and lower cost options for interplanetary exploration are needed. Capitalizing on the technology miniaturization trends and the SmallSat class of vehicles could provide advancements for interplanetary space exploration. Presented here, are the results of a feasibility study conducted during an internship at NASA Langley Research Center that explored the use of a SmallSat-sized Hypersonic Inflatable Aerodynamic Decelerator (HIAD) to enable interplanetary orbital science missions via aerocapture.

Shelly C. Mann↗