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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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Information is given in viewgraph form on the Common Lunar Lander (CLL) engineering study results. The mission is to provide a delivery system to soft-land a 200 kg payload set at any given lunar latitude and longitude. Topics covered include the study schedule, mission goals and requirements, the CLL reference mission, costs, CLL options, and two stage performance analysis.
Common Lunar Lander trajectory analysis is presented in viewgraph format. Trajectory requirements, trajectory characteristics, trajectory timeline, and alternate trajectory advantages and disadvantages are given.
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.
A discussion of the tracking system for Artemis (the Common Lunar Lander) is presented. Among the topics presented are the following: major drivers for system definition, results of vendor survey, baseline system properties, program considerations, and mission phases requiring tracking.
Information is given in viewgraph form on a nickel-hydrogen common pressure vessel spaceflight experiment. Information given includes the schedule and diagrams of the electrical power subsystem and control features.
Information is given in viewgraph form on the nickel hydrogen common pressure vessel (CPV) 2.5V twin stack cell designs. Information given includes an energy analysis, a CPV design comparison, a summary of CPV characterization testing, a comparison of discharge voltage among designs, and life test performance summaries.
The Common Berthing Mechanism (CBM) is a generic device used to join the pressurized elements of the Space Station Freedom (SSF) utilizing the Space Shuttle Orbiter Remote Manipulator System (SRMS) or the Space Station Remote Manipulator System (SSRMS). The two berthing halves, the active, and the passive, maintain a pressurized atmosphere to allow astronaut passage, as well as to provide a structural linkage between elements. The generic design of the CBM allows any Passive Berthing Mechanism to berth with any Active Berthing Mechanism, permitting a variety of pressurized module patterns to be built.
An economic analysis examines a reusable single crew module to reduce the cost of Moon to stay exploration by 5 billion dollars. Topics covered in viewgraph format include the following: aerodynamics, weight, runway landing, technology support, and common module reentry requirements.
The purpose of this work was to demonstrate the feasibility of vapor-phase reduction (pyrolysis) of lunar materials to produce oxygen. Solar furnace experiments were conducted on two common lunar minerals, ilmenite and anorthite. Thermodynamic equilibrium calculations predicted that ilmenite should show a larger pressure increase than anorthite under conditions of the experiments and this was confirmed by the experiments. The measured mass loss of the ilmenite sample was consistent with loss of oxygen by reduction of iron in the liquid phase; this result was also predicted from equilibrium calculations. Based on preliminary experiments and equilibrium calculations, the temperatures needed for pyrolysis are expected to be in the range of 2000 to 2500 K, giving total gas pressures of 0.01 to 1 torr. Bulk regolith can be used as a feedstock without extensive beneficiation. Further, selective condensation of metal-containing species from the gas phase may yield metallic iron and silicon as byproducts from the process.
The excitation of oscillatory modes by a low-mass star orbiting inside a common envelope with a more massive star is investigated, with emphasis on adiabatic high spherical harmonic degree (l is much greater than 1) modes propagating outward in the envelope. The dominant oscillatory modes are those for which the spherical harmonic order is large, and thus the amplitudes are large close to the equatorial plane and small closer to the poles. A secondary of mass about 1 percent of the primary mass excites modes with relative surface amplitudes of a few x 10 percent. Even a Jupiter-like brown dwarf, when it is very deep in the envelope of an asymptotic giant branch star, can cause perturbations of relative surface amplitudes of about 10 percent near the equatorial plane. If mass loss is influenced by oscillation, then this mechanism can lead to higher mass loss in the equatorial plane. In case of an asymptotic giant branch primary, this might lead to the formation of an elliptical planetary nebula.
Over 7000 low-earth-orbit (LEO) cycles were demonstrated on a full-size aerospace common pressure vessel (CPV) prototype. The battery demonstrated the capability of the basic CPV design to meet the life and reliability requirements of aerospace missions. Subsequent design modifications have been employed to address the shortcomings of the original design and several new prototypes have been fabricated. These include a 12-cell 125 amp-hour geosynchronous earth-orbit (GEO) battery and a 22-cell 10.5 amp-hour LEO battery. Cells for an 80-cell battery intended to demonstrate the high voltage capability of the CPV design have also been fabricated. In addition, assembly of a 20-cell aircraft starting battery prototype is in progress, and testing of a group of 12-volt, 160 amp-hour terrestrial batteries is continuing.
Common scaling criterion found to relate some physical quantities characterizing tensile failures of three different solid propellant materials. Tensile failures of different rubbery propellants characterized by similar plots.
The Austin Cynthesis Corporation was formed to respond to a Request for Proposal for the design of a Common Lunar Lander (CLL) capable of carrying lightweight (less than 500 kg), unspecified payload to the moon. This Final Design Report Document includes information on the requirements for the design project; the ideas proposed as solutions to the design problem; the work which has been completed in support of the design effort; justifications, validations, and verifications of decisions made during the project; and suggestions for future work to be done in support of the project. A project schedule, including current status of the items included on the schedule, as well as cost and management summaries is also included.
The common mode rejection ratio (CMRR) of the single operational amplifier (op amp) differential amplifier and of the three operational amplifier differential amplifier was investigated. The three op amp differential amplifier circuit is used in the signal conditioner circuit which amplifies signals such as the electromyograph or electrocardiogram. The investigation confirmed via SPICE modeling what has been observed by others in the recent literature that the CMRR for the circuit can be maximized without precision resistor values or precisely matched op amps. This can be done if one resistor in the final stage can be adjusted either by a potentiometer or by laser trimming in the case of hybrid circuit fabrication.
A two-dimensional and time-dependent thermal model of a multicell common pressure vessel (CPV) nickel-hydrogen battery was developed. A finite element solver called PDE/Protran was used to solve this model. The model was used to investigate the effects of various design parameters on the temperature profile within the cell. The results were used to help find a design that will yield an acceptable temperature gradient inside a multicell CPV nickel-hydrogen battery. Steady-state and unsteady-state cases with a constant heat generation rate and a time-dependent heat generation rate were solved.
The technology background and design qualification of the multicell common pressure vessel nickel hydrogen battery are described. The results of full flight qualification, including random vibration at 19.5 g for two minutes in each axis, electrical characterization in a thermal vacuum chamber, and mass spectroscopy vessel leak detection are reviewed and 12.7 cm qualification and 25.4 cm design adaptation are discussed.
The Common Lunar Lander (CLL) is a concept for a small, unpiloted vehicle which would provide a low-cost capability to land any of a variety of payloads in the 200 kg class at any point on the surface of the moon. Initiated as a precursor mission for the First Lunar Outpost, it also has considerable potential for use by the scientific community at large. A series of studies has been conducted at the NASA Johnson Space Center to define initial requirements and to initiate the design process. This paper describes the propulsion subsystem design as it existed at the CLL System Design Review. The propulsion subsystem design is described in detail along with the planned operations concept, including the unique concept of using pulsing of main engines for thrust modulation. Design options and trades considered and the verification process philosophy which was being planned for the program are discussed.
This paper presents the results of tests of six commonly used airfoils: the CYH, the N-22, the C-72, the Boeing 106, and the Gottingen 398. The lifts, drags, and pitching moments of the airfoils were measured through a large range of positive and negative angles of attack. The tests were made in the variable density wind tunnel of the National Advisory Committee for Aeronautics at a large Boeing 106, and the Gottingen 398 airfoils, the negative maximum lift coefficients were found to be approximately half the positive; but for the M-6 and the CYH, which have less effective values were, respectively, 0.8 and 0.6 of the positive values.