Electric propulsion - Systems, flight mechanics, power source, and mission applications
Electric propulsion systems and spacecraft power sources, flight mechanics, and mission applications
Stuhlinger, E.↗
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.
Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.
Evolution of propulsion systems and the detonation process.
Detonation research in rocket propulsion systems, discussing gas dynamics of explosion harnessing
Oppenheim, A. K.↗
Optimal space flight with multiple propulsion systems.
Optimal space flight conditions for vehicles using multiple propulsion systems, noting performance of solar electric vehicle in Jupiter probe
Hazelrigg, G. A., Jr.↗
Effects of sterilization and decontamination on hydrazine propulsion systems.
Catalyst poisoning and hydrazine material compatibility during hydrazine propulsion systems sterilization and decontamination
Heinz, M. H.↗
Apollo 7 CSM 101 service propulsion system, flight evaluation
Flight performance of command module service propulsion system during Apollo 7 mission
Source record↗
Low thrust /high-impulse/ nuclear and electric space propulsion systems
Low thrust high impulse nuclear and electric space propulsion systems, discussing performance capability for space missions
Moeckel, W. E.↗
Design considerations and requirements for integrating an electric propulsion system into the SERT II and future spacecraft
Electric propulsion systems integration into SERT 2 spacecraft, discussing launch imposed environment, thrust vector control, thrustor breakdown, power conditioning, etc
Rulis, R. J.↗
Development of onboard equipment for space shuttle propulsion systems
Development of onboard checkout equipment for space shuttle propulsion systems
Source record↗
Apollo Service Propulsion System Rocket Engine Bipropellant Valve Improvement Program
Apollo service propulsion system rocket engine bipropellant valve improvement program - valve design guide and oxygen-hydrogen technology
Source record↗
Solar electric propulsion system /SEPS/ program plans and system definition
The status of the NASA Solar Electric Propulsion System (SEPS) program is reviewed. The plans for SEPS definition and development include the initiation of the SEPS definition phase, the procurement for full-scale development in 1980, delivery of the SEPS for integration and tests with the comet rendezvous spacecraft in 1984, and a launch in 1985 that involves a flyby of Halley's comet in 1985 and a subsequent rendezvous with the comet Tempel 2 in 1988. In preparation for this, the acquisition process for SEPS has been initiated based on mission requirements rather than system requirements.
Austin, R. E.↗
Propfan test assessment propfan propulsion system static test report
The propfan test assessment (PTA) propulsion system successfully completed over 50 hours of extensive static ground tests, including a 36 hour endurance test. All major systems performed as expected, verifying that the large-scale 2.74 m diameter propfan, engine, gearbox, controls, subsystems, and flight instrumentation will be satisfactory with minor modifications for the upcoming PTA flight tests on the GII aircraft in early 1987. A test envelope was established for static ground operation to maintain propfan blade stresses within limits for propfan rotational speeds up to 105 percent and power levels up to 3880 kW. Transient tests verified stable, predictable response of engine power and propfan speed controls. Installed engine TSFC was better than expected, probably due to the excellent inlet performance coupled with the supercharging effect of the propfan. Near- and far-field noise spectra contained three dominant components, which were dependent on power, tip speed, and direction. The components were propfan blade tones, propfan random noise, and compressor/propfan interaction noise. No significant turbine noise or combustion noise was evident.
Orourke, D. M.↗
Space Station propulsion system test bed
The test bed to study H2/O2 propulsion technology for the Space Station is discussed. The test bed consists of propellant accumulators, valving, instrumentation, and controls configured in a 9-ft cube. A water electrolysis module was added to simulate the baseline propulsion system configuration. The activation of the test bed is described, and results are presented from tests of the system, including verification of the control system, thruster tests, electrolysis system testing, and acceptance test, oxidizer system, and fuel system blowdowns.
Norman, A. M.↗
Probabilistic structural analysis methods for space transportation propulsion systems
Information on probabilistic structural analysis methods for space propulsion systems is given in viewgraph form. Information is given on deterministic certification methods, probability of failure, component response analysis, stress responses for 2nd stage turbine blades, Space Shuttle Main Engine (SSME) structural durability, and program plans. .
Chamis, C. C.↗
Common Lunar Lander (CLL) Propulsion System
A description of the Common Lunar Lander (CLL) propulsion system is given. Among the topics discussed are the following: system characteristics, system mission requirements, key drivers to subsystem selection, system readiness level, and point design output. Additionally, a schematic of the system is provided.
Hyatt, Don↗
A probabilistic approach to the evaluation of fatigue damage in a space propulsion system injector element
The fatigue damage of a space propulsion system component is computed using probabilistic structural analysis methods. The analysis takes into account the variations in static and dynamic loads, the uncertainty in structural damping, and the scatter in material fatigue resistance. The key elements of the probabilistic approach include: (1) a numerical engine model for describing the global component interface loads consistent with engine balance, (2) models for computing the local mode boundary conditions on the component, (3) a static structural analysis model that captures the strains at a damage critical location as a function of engine performance variables, (4) a finite element model for assessment of the random amplitude stress response due to random base and pressure excitations with uncertain power and correlation length, and (5) advanced first order reliability methods for computing the probabilities associated with the fatigue damage.
Rajagopal, K. R.↗
Reliability analysis techniques for engine-out failures in main propulsion systems
Reliability formulas are derived for a liquid main propulsion system consisting of n engines, which allows for mission success in the event a single-engine controlled shutdown occurs afer some given time. The formulas include terms to reflect different reliabilities at different engine power levels, startup and throttling reliabilities, benign and catastrophic failures, and failure-distribution scale and shape parameters. These formulas can be used for reliability analyses and sensitivity studies. A parametric launch-vehicle reliability-comparison technique for conceptual preliminary design studies is also described.
Lee, Robert A.↗
Intelligent neuroprocessors for in-situ launch vehicle propulsion systems health management
Efficacy of existing on-board propulsion systems health management systems (HMS) are severely impacted by computational limitations (e.g., low sampling rates); paradigmatic limitations (e.g., low-fidelity logic/parameter redlining only, false alarms due to noisy/corrupted sensor signatures, preprogrammed diagnostics only); and telemetry bandwidth limitations on space/ground interactions. Ultra-compact/light, adaptive neural networks with massively parallel, asynchronous, fast reconfigurable and fault-tolerant information processing properties have already demonstrated significant potential for inflight diagnostic analyses and resource allocation with reduced ground dependence. In particular, they can automatically exploit correlation effects across multiple sensor streams (plume analyzer, flow meters, vibration detectors, etc.) so as to detect anomaly signatures that cannot be determined from the exploitation of single sensor. Furthermore, neural networks have already demonstrated the potential for impacting real-time fault recovery in vehicle subsystems by adaptively regulating combustion mixture/power subsystems and optimizing resource utilization under degraded conditions. A class of high-performance neuroprocessors, developed at JPL, that have demonstrated potential for next-generation HMS for a family of space transportation vehicles envisioned for the next few decades, including HLLV, NLS, and space shuttle is presented. Of fundamental interest are intelligent neuroprocessors for real-time plume analysis, optimizing combustion mixture-ratio, and feedback to hydraulic, pneumatic control systems. This class includes concurrently asynchronous reprogrammable, nonvolatile, analog neural processors with high speed, high bandwidth electronic/optical I/O interfaced, with special emphasis on NASA's unique requirements in terms of performance, reliability, ultra-high density ultra-compactness, ultra-light weight devices, radiation hardened devices, power stringency, and long life terms.
Gulati, S.↗
NASA Lewis Propulsion Systems Laboratory Customer Guide Manual
This manual describes the Propulsion Systems Laboratory (PSL) at NASA Lewis Research Center. The PSL complex supports two large engine test cells (PSL-3 and PSL-4) that are capable of providing flight simulation to altitudes of 70,000 ft. Facility variables at the engine or test-article inlet, such as pressure, temperature, and Mach number (up to 3.0 for PSL-3 and up to 6.0 planned for PSL-4), are discussed. Support systems such as the heated and cooled combustion air systems; the altitude exhaust system; the hydraulic system; the nitrogen, oxygen, and hydrogen systems; hydrogen burners; rotating screen assemblies; the engine exhaust gas-sampling system; the infrared imaging system; and single- and multiple-axis thrust stands are addressed. Facility safety procedures are also stated.
Soeder, Ronald H.↗