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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 37 records · Page 2
All sourcesNASA NTRSDOE OSTI
NASA NTRS2006

A Water Recovery System Evolved for Exploration

A new water recovery system designed towards fulfillment of NASA's Vision for Space Exploration is presented. This water recovery system is an evolution of the current state-of-the-art system. Through novel integration of proven technologies for air and water purification, this system promises to elevate existing technology to higher levels of optimization. The novel aspect of the system is twofold: Volatile organic contaminants will be removed from the cabin air via catalytic oxidation in the vapor phase, prior to their absorption into the aqueous phase, and vapor compression distillation technology will be used to process the condensate and hygiene waste streams in addition to the urine waste stream. Oxidation kinetics dictate that removal of volatile organic contaminants from the vapor phase is more efficient. Treatment of the various waste streams by VCD will reduce the load on the expendable ion exchange and adsorption media which follow, and on the aqueous-phase volatile removal assembly further downstream. Incorporating these advantages will reduce the weight, volume, and power requirements of the system, as well as resupply.

ORourke, Mary Jane E.↗
NASA NTRS2001

A Low Cost, Self Acting, Liquid Hydrogen Boil-Off Recovery System

The purpose of this research was to develop a prototype liquid hydrogen boll-off recovery system. Perform analyses to finalize recovery system cycle, design detail components, fabricate hardware, and conduct sub-component, component, and system level tests leading to the delivery of a prototype system. The design point and off-design analyses identified cycle improvements to increase the robustness of the system by adding a by-pass heat exchanger. Based on the design, analysis, and testing conducted, the recovery system will liquefy 31% of the gaseous boil off from a liquid hydrogen storage tank. All components, including a high speed, miniature turbocompressor, were designed and manufacturing drawings were created. All hardware was fabricated and tests were conducted in air, helium, and hydrogen. Testing validated the design, except for the turbocompressor. A rotor-to-stator clearance issue was discovered as a result of a concentricity tolerance stack-up.

Pelfrey, Joy W.↗
NASA NTRS1971

Spacecraft oxygen recovery system

Spacecraft closed loop oxygen recovery system using electrochemical carbon dioxide concentrator, Sabatier reactor and water electrolysis subsystem

Quattrone, P. D.↗
NASA NTRS2007

Water Recovery Systems for Exploration Missions

As NASA prepares for the Vision for Space Exploration, advances in technology for water recovery systems are necessary to enable future missions. This paper examines the proposed water recovery systems for the initial Constellation exploration missions as well as the capability gaps that exist in the current technology portfolio. We discuss how these gaps will be addressed with future technology development. In addition, the paper reviews how the water recovery system matures throughout the sequence of planned exploration missions, to ultimately support a 180-day lunar mission.

Pickering, Karen D.↗
NASA NTRS1989

Advanced Recovery Systems for Advanced Launch Vehicles (ARS) phase 1 study results

The paper documents the work completed during the Advanced Recovery Systems for Advanced Launch Vehicles phase 1 study. Particular attention is given to the definition of the design of a single recovery system for the most likely near-term payload, a propulsion/avionic module (P/AM). A P/AM recovery system for phase 2 demonstration was designed which offers low cost, extremely low weight, good performance, potential for pinpoint loading, and operational flexibility.

Wailes, William K.↗
NASA NTRS1975

Evaluation of all-parachute and hybrid /parachute-retrorocket/ recovery systems for a one-million-pound booster

Both an all-parachute recovery system and a hybrid parachute-retrorocket recovery system for a one-million-pound booster are evaluated in order to determine what parachute sizes and number in a cluster are required for an all-parachute system to provide impact velocities of less than 100 ft/sec and in order to determine whether the hybrid system permits a weight reduction over an all-parachute system. A minimum-weight hybrid decelerator system using Kevlar materials for a cluster of three parachutes with two stages of reefing is analyzed. Major conclusions are that for an impact velocity of less than 100 ft/sec the hybrid decelerator system is lighter in weight, and that the use of Kevlar rather than Nylon material results in hybrid decelerator system weight savings of over 40% for impact velocities in the range 60-30 ft/sec.

Eckstrom, C. V.↗
NASA NTRS2005

Design, Development and Flight Testing of the U.S. Army 4200 sq ft Parafoil Recovery System

The purpose of this paper is to describe the design, development and flight-testing of the U.S. Army 4200 sq ft parafoil recovery system built under NASA Contract NAS 9-00076. The 4200 f? parafoil described herein was a potential candidate to fulfill the U.S. Army requirement for a 10,000 lb useable payload precision guided recovery system. Design heritage as well as specific features, like lower surface inlets, confluence fitting, upper surface energy modulator design, deployment bag design and 60 ft diameter Ringslot drogue will be discussed. Initial flight test results, ground testing of various components to verify design margin and configuration changes will also be discussed. The 4200 sq ft parafoil recovery system completed three flight tests during 2003 at payload weights of over 15,000 Ibs

Bennett, Thomas W.↗
NASA NTRS2007

Design, Development & Flight Testing Of The U.S. Army 4200 sq ft Parafoil Recovery System

The purpose of this paper is to describe the design, development and flight testing of the U.S. Army 4200 ft(sup 2) parafoil recovery system built under NASA Contract NAS9-00076. The 4200 ft(sup 2) parafoil described herein was a potential candidate to fulfill the U.S. Army requirement for a 10,000 lb useable payload precision guided recovery system. Design heritage as well as specific features, like lower surface inlets, confluence fitting, upper surface energy modulator design, deployment bag design and 60 ft diameter Ringslot drogue will be discussed. Initial flight test results, ground testing of various components to verify design margin and configuration changes will also be discussed. The 4200 ft(sup 2) parafoil recovery system completed three flight tests during 2003 at payload weights of over 15,000 lbs.

Bennett, Thomas W.↗
NASA NTRS1970

Aerobee 350 recovery system Final project report

Aerobee 350 recovery system comprising paraloon and extended skirt parachute deceleration devices and incorporating electrical control, pyrotechnic, and pneumatic subsystems - tests

Source record↗
NASA NTRS2016

Upgrades to the ISS Water Recovery System

The International Space Station Water Recovery System (WRS) is comprised of the Water Processor Assembly (WPA) and the Urine Processor Assembly (UPA). The WRS produces potable water from a combination of crew urine (first processed through the UPA), crew latent, and Sabatier product water. Though the WRS has performed well since operations began in November 2008, several modifications have been identified to improve the overall system performance. These modifications can reduce resupply and improve overall system reliability, which is beneficial for the ongoing ISS mission as well as for future NASA manned missions. The following paper details efforts to reduce the resupply mass of the WPA Multifiltration Bed, develop improved catalyst for the WPA Catalytic Reactor, evaluate optimum operation of UPA through parametric testing, and improve reliability of the UPA fluids pump and Distillation Assembly.

Kayatin, Matthew J.↗
NASA NTRS1975

Effects of 1980 technology on weight of a recovery system for a one million pound booster

The effects were evaluated of 1980 technology on the weight of recovery systems capable of decelerating a one-million-pound booster to vertical velocities of 60 or 30 ft/sec at sea level impact. A nominal set of booster staging conditions were assumed and there were no constraints on parachute size, number or type. The effects of new materials that would be available by 1980, the effects of booster attitude during entry, various parachute staging methods, parachute reefing schemes, parachute-retro rocket hybrid systems, and the effects of dividing the booster into separate pieces for recovery were evaluated. It was determined that for the systems considered, a hybrid parachute-retro-rocket recovery system would have the minimum weight. New materials now becoming available for parachute fabrication should result in a 37-percent reduction in hybrid recovery system weight for an impact velocity of 30 fps.

Eckstrom, C. V.↗
NASA NTRS1991

Liquid booster engine reuse - A recovery system

The paper presents the design of a recovery system for a suborbital payload of an Atlas E rocket. This program utilizes off-the-shelf and previously qualified avionics, flotation, and decelerator systems. A brief history of liquid-engine recoveries is presented first, then the system design utilizing two self-contained structurally-identical pods diametrically mounted to the thrust section is outlined. A mortar-deployed drogue and the main parachute are described, and experimental procedures are considered. Data obtained from one tricluster drop employing a cylindrical test vehicle and helicopter is analyzed, and a satisfactory load balance between the parachutes is observed.

Von Eckroth, Wulf↗
NASA NTRS2007

Status of the Regenerative ECLSS Water Recovery System

NASA is developing a regenerative water recovery system (WRS) for deployment on the International Space Station (ISS), The major assemblies included in this system are the Water Processor Assembly (WPA) and Urine Processor Assembly (UPA). The WPA has been developed by Hamilton Sundstrand Space Systems International (HSSSI), Inc., while the UPA has been developed by the Marshall Space Flight Center (MSFC). Test and verification activities have been completed for the system and planning for launch and on-orbit activation is underway. This paper summarizes the status as of April 2007 and describes some of the technical challenges encountered and lessons learned over the past year.

Bagdigian, Robert M.↗
NASA NTRS2017

Upgrades to the International Space Station Water Recovery System

The International Space Station (ISS) Water Recovery System (WRS) includes the Water Processor Assembly (WPA) and the Urine Processor Assembly (UPA). The WRS produces potable water from a combination of crew urine (first processed through the UPA), crew latent, and Sabatier product water. Though the WRS has performed well since operations began in November 2008, several modifications have been identified to improve the overall system performance. These modifications aim to reduce resupply and improve overall system reliability, which is beneficial for the ongoing ISS mission as well as for future NASA manned missions. The following paper details efforts to improve the WPA through the use of reverse osmosis membrane technology to reduce the resupply mass of the WPA Multi-filtration Bed and improved catalyst for the WPA Catalytic Reactor to reduce the operational temperature and pressure. For the UPA, this paper discusses progress on various concepts for improving the reliability of the system, including the implementation of a more reliable drive belt, improved methods for managing condensate in the stationary bowl of the Distillation Assembly, and evaluating upgrades to the UPA vacuum pump.

Kayatin, Matthew J.↗