Electrostatic propulsion system with a direct nuclear electrogenerator Patent
Nuclear electric generator for accelerating charged propellant particles in electrostatic propulsion system
Low, C. A., Jr.↗
SEARCH · Engineering Papers
Results for “Propulsion System”
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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Apollo service propulsion system rocket engine bipropellant valve improvement program Final report
Rocket engine bipropellant valve improvement for Apollo service propulsion system
Source record↗
Survey of materials for hydrazine propulsion systems in multicycle extended life applications
An assessment is presented of materials compatibility data for hydrazine monopropellant propulsion systems applicable to the Space Shuttle vehicle missions. Materials were evaluated for application over a 10-yr/100-mission operational lifetime with minimum refurbishment. A general materials compatibility rating for a broad range of materials and several propellants based primarily on static liquid propellant immersion testing and an in-depth evaluation of hydrazine decomposition as a function of purity, temperature, material, surface conditions, etc., are presented. The most promising polymeric material candidates for propellant diaphragms and seals appear to have little effect on increasing hydrazine decomposition rates, but the materials themselves do undergo changes in physical properties which can affect their 10-yr performance in multicycle applications. The available data on these physical properties of elastomeric materials as affected by exposure to hydrazine or related environments are presented.
Coulbert, C. D.↗
Apollo 12 mission report: Descent, propulsion system final flight evaluation (supplement 5)
The results are presented of the postflight analysis of the Descent propulsion system (DPS) performance during the Apollo 12 Mission. The primary objective of the analysis was to determine the steady-state performance of the DPS during the descent phase of the manned lunar landing. This is a supplement ot the Apollo 12 Mission Report. In addition to further analysis of the DPS, this report brings together information from other reports and memorandums analyzing specific anomalies and performance in order to present a comprehensive description of the DPS operation during the Apollo 12 Mission.
Seto, R. K. M.↗
Automatic arc welding of propulsion system tubing in close proximity to sensitive electronic devices
The planned final assembly of the Galileo spacecraft propulsion system tubing, which involves welding in close proximity to sensitive electronics, raised significant concerns about the effects of electromagnetic coupling of weld energy on CMOS and other sensitive integrated circuits. A test program was established to assess the potential of an orbital arc welder and an RF-induction brazing machine to damage sensitive electronic equipment. Test parameters were varied to assess the effectiveness of typical transient suppression practices such as grounding, bonding, and shielding. A technique was developed to calibrate the hazard levels at the victim-circuit location; this technique is described along with the results and conclusions of the test program.
Lumsden, J. M.↗
Recent propulsion system flight tests at the NASA Dryden Flight Research Center
The article presents a summary of the propulsion system tests conducted on a number of aircraft at the NASA Dryden Flight Research Center. The tests included digital engine control systems, engine-inlet compatibility, inlet-airframe interactions, nozzle-boattail drag and advanced turboprop acoustics. Among the aircraft evaluated were the F-15, HiMAT, F-14, and the JetStar.
Burcham, F. W., Jr.↗
Evaluation of propellent tank insulation concepts for low-thrust chemical propulsion systems: Executive summary
Cryogenic propellant tank insulations or liquid oxygen/liquid hydrogen low-thrust 2224N (500 lbf) propulsion systems (LTPS) were assessed. The insulation studied consisted of combinations of N2-purged foam and multilayer insulation (MLI) as well as He-purged MLI-only. Heat leak and payload performance predictions were made for three shuttle-launched LTPS designed for shuttle bay packaged payload densities of 56 kg cu/m (3.5 lbm/cu ft), 40 kg/cu m (2.5 lbm/cu ft) and 24 kg/cu m (1.5 lbm/cu ft). Foam/MLI insulations were found to increase LTPS payload delivery capability when compared with He-purged MLI-only. An additional benefit of foam/MLI was reduced operational complexity because orbiter cargo bay N2 purge gas could be used for MLI purging. Maximum payload mass benefit occurred when an enhanced convection, rather than natural convection, heat transfer was specified for the insulation purge enclosure. The enhanced convection environment allowed minimum insulation thickness to be used for the foam/MLI interface temperature selected to correspond to the moisture dew point in the N2 purge gas. Experimental verification of foam/MLI benefits was recommended. A conservative program cost estimate for testing a MLI-foam insulated tank was 2.1 million dollars. This cost could be reduced significantly without increasing program risk.
Kramer, T.↗
Lunar missions using advanced chemical propulsion - System design issues
In this paper, the masses in low earth orbit (LEO) were compared for several propulsion systems: nitrogen tetroxide/monomethyl hydrazine, oxygen/methane, oxygen/hydrogen, and metallized O2/H2/Al propellants. Also, the payload mass increases enabled with these systems were addressed. In addition, many system design issues involving the engine thrust levels, engine commonality between the transfer vehicle and the excursion vehicle, and the number of launches to place the lunar mission vehicles into LEO are discussed. Analyses of small lunar missions launched from a single STS-C flight are also presented.
Palaszewski, Bryan↗
Probabilistic simulation of concurrent engineering of propulsion systems
Technology readiness and the available infrastructure is assessed for timely computational simulation of concurrent engineering for propulsion systems. Results for initial coupled multidisciplinary, fabrication-process, and system simulators are presented including uncertainties inherent in various facets of engineering processes. An approach is outlined for computationally formalizing the concurrent engineering process from cradle-to-grave via discipline dedicated workstations linked with a common database.
Chamis, C. C.↗
Configuration Management File Manager Developed for Numerical Propulsion System Simulation
One of the objectives of the High Performance Computing and Communication Project's (HPCCP) Numerical Propulsion System Simulation (NPSS) is to provide a common and consistent way to manage applications, data, and engine simulations. The NPSS Configuration Management (CM) File Manager integrated with the Common Desktop Environment (CDE) window management system provides a common look and feel for the configuration management of data, applications, and engine simulations for U.S. engine companies. In addition, CM File Manager provides tools to manage a simulation. Features include managing input files, output files, textual notes, and any other material normally associated with simulation. The CM File Manager includes a generic configuration management Application Program Interface (API) that can be adapted for the configuration management repositories of any U.S. engine company.
Follen, Gregory J.↗
An Approach for Utilizing Power Flow Modeling for Simulations of Hybrid Electric Propulsion Systems
This paper describes an approach to creating simulations of the electric components for a hybrid electric propulsion system. The proposed modeling technique is based on power/load flow modeling and is designed to provide a modular framework that includes buses, lines, and other electrical components that can be connected together to form the electrical distribution system. The purpose of this paper is to detail an electric distribution system modeling technique and to demonstrate how these models may be integrated with turbomachinery simulations. These general modeling techniques were created to be utilized for system and control design studies. Additionally, steady-state and dynamic performance for a proposed model example is compared with data from a hardware in the loop simulation.
Chapman, Jeffryes W.↗
Particle Size Measurements from the 2018 Honeywell Uncertified Research Engine Test in the NASA Propulsion Systems Laboratory
The particle size measurements from the Honeywell Uncertified Research Engine Icing Test in the NASA Propulsion Systems Laboratory conducted in 2018 are presented. This work focuses on describing the experimental arrangement, the processing and analysis methods, and final results for select cases acquired during ice crystal cloud conditions. The measurements presented will include data acquired by two High Speed Imaging instruments located both upstream and downstream of the fan, in the engine bypass section. Experimental results demonstrate the expected downward shift in the particle size distribution as the cloud passes through the engine fan and the ice particles break-up. This work also demonstrates the feasibility of acquiring particle size distributions in the environment of a running engine.
Engine icing↗
Standardization - A method of reducing auxiliary propulsion systems costs
This paper deals with the efforts of the National Aeronautics and Space Administration to take advantage of the economies made possible by the Space Shuttle by reducing the costs of acquiring and flying payloads for the Shuttle. Specifically, the paper addresses the route that NASA's Low Cost Systems Office is following in order to reduce the cost of auxiliary propulsion systems. This approach emphasizes the establishment of standard hardware items, which will be used on as many spacecraft as possible. The method by which a standard is selected and how it is maintained as a standard are discussed. The process by which the 5 Newton hydrazine thruster was adopted is described, as a typical example.
Jones, L. W.↗
Method for providing real-time control of a gaseous propellant rocket propulsion system
The new and improved methods and apparatus disclosed provide effective real-time management of a spacecraft rocket engine powered by gaseous propellants. Real-time measurements representative of the engine performance are compared with predetermined standards to selectively control the supply of propellants to the engine for optimizing its performance as well as efficiently managing the consumption of propellants. A priority system is provided for achieving effective real-time management of the propulsion system by first regulating the propellants to keep the engine operating at an efficient level and thereafter regulating the consumption ratio of the propellants. A lower priority level is provided to balance the consumption of the propellants so significant quantities of unexpended propellants will not be left over at the end of the scheduled mission of the engine.
Morris, Brian G.↗
Development of Metal Matrix Composites for NASA's Advanced Propulsion Systems
The state-of-the-art development of several Metal Matrix Composites (MMC) for NASA's advanced propulsion systems will be presented. The goal is to provide an overview of NASA-Marshall Space Flight Center's on-going activities in MMC components for advanced liquid rocket engines such as the X-33 vehicle's Aerospike engine and X-34's Fastrac engine. The focus will be on lightweight, low cost, and environmental compatibility with oxygen and hydrogen of key MMC materials, within each of NASA's new propulsion application, that will provide a high payoff for NASA's Reusable Launch Vehicles and space access vehicles. In order to fabricate structures from MMC, effective joining methods must be developed to join MMC to the same or to different monolithic alloys. Therefore, a qualitative assessment of MMC's welding and joining techniques will be outlined.
Lee, J.↗
Thermionic reactor ion propulsion system /TRIPS/ - Its multi-mission capability.
The unmanned planetary exploration to be conducted in the last two decades of this century includes many higher energy missions which tax all presently available propulsion systems beyond their limit. One candidate with the versatility and performance to meet these mission objectives is nuclear electric propulsion (NEP). Additionally, the NEP System is feasible in orbit raising operations with the Shuttle or Shuttle/Tug combination. A representative planetary mission is described (Uranus-Neptune flyby with probe), and geocentric performance and tradeoffs are discussed. The NEP System is described in more detail with particular emphasis on the power subsystem consisting of the thermionic reactor, heat rejection subsystem, and neutron shield.
Peelgren, M. L.↗
Injector orifice study, Apollo service propulsion system Summary report, 7 Apr. 1967 - 31 Jul. 1968
Environmental tests on designed hydraulic injector for Apollo service propulsion system
Source record↗
Sterilizable Liquid Propulsion System, Part 1 Final Report, 5 Oct. 1966 - 31 Mar. 1968
Exposure of assembled and fueled bipropellant liquid propulsion system to ethylene oxide
Brady, F.↗