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All sourcesNASA NTRSDOE OSTI
NASA NTRS1989

LACE flight dynamics experiment

The Low Power Atmospheric Compensation Experiment (LACE) is scheduled for launch in late 1989 into a 556 km altitude circular orbit of 43 deg inclination. The LACE flight dynamics experiment is an experiment secondary to the primary LACE mission. The purpose of the experiment is to provide on-orbit systems identification of the LACE spacecraft. The structure of the LACE spacecraft is of special interest to the CSI community. It incorporates 3 deployable/retractable booms of maximum length 45.72 m (150 ft) mounted on a rectangular parallelepiped bus of mass 1,200 kg. The zenith directed gravity gradient boom is mounted on the top of the bus; the retroreflector boom is mounted forward and deployed along the velocity vector, the balance boom is mounted and pointed aft. Attitude stabilization is accomplished by means of gravity gradient torques and by a momentum wheel. The LACE flight dynamics experiment is designed to measure modal frequencies, damping ratios, and oscillation amplitudes of the LACE spacecraft, as well as the vibration intensity generated by boom deployments and retractions. It is anticipated that this experiment will provide an opportunity for improvements in the accuracy of computer simulations of flexible structures and multibody dynamics.

Fisher, Shalom↗
NASA NTRS1992

Control-structures Interaction Test of the LACE Satellite

It is clear that additional experience and validation of Control Structures Interaction (CSI) techniques are needed in controlling the structural dynamics of flexible spacecraft. It is also clear that the effects of the space environment such as weightlessness dictate that this be done in space. Unfortunately, orbital tests are difficult to achieve because of the high cost of the test article, the launch into orbit, the instrumentation, and communication systems. The Low-power Atmospheric Compensation Experiment (LACE) Satellite has provided an opportunity to achieve a CSI test in space for very little cost. First, the CSI test rode piggy-back and did not interfere with the primary objective of LACE. Second, the novel technique of using ground based measurements of vibration of the orbiting satellite was employed. The LACE has a heavy central body to which is attached booms with lengths as long as 150 feet. The ground measurements were obtained using laser Doppler radar at the MIT Lincoln Laboratory Firepond Facility. The initial tests demonstrated the accuracy of the vibration measurements and obtained structural responses for enhancing the accuracy of the mathematical model of the structural dynamics. Germanium corner-cube retroreflectors attached to the central body and a boom deployed to 18 feet ensured a high strength return signal. Subsequent tests demonstrated the ability of an open-loop damper to attenuate the vibrations of the orbiting satellite. The LACE test results are important in contributing to the validation of a CSI technique, and demonstrating a novel ground measurement technique for orbital tests that is accurate but which has very low cost.

Taylor, Lawrence W., Jr.↗
NASA NTRS1993

Accurate attitude determination of the LACE satellite

The Low-power Atmospheric Compensation Experiment (LACE) satellite, launched in February 1990 by the Naval Research Laboratory, uses a magnetic damper on a gravity gradient boom and a momentum wheel with its axis perpendicular to the plane of the orbit to stabilize and maintain its attitude. Satellite attitude is determined using three types of sensors: a conical Earth scanner, a set of sun sensors, and a magnetometer. The Ultraviolet Plume Instrument (UVPI), on board LACE, consists of two intensified CCD cameras and a gimbal led pointing mirror. The primary purpose of the UVPI is to image rocket plumes from space in the ultraviolet and visible wavelengths. Secondary objectives include imaging stars, atmospheric phenomena, and ground targets. The problem facing the UVPI experimenters is that the sensitivity of the LACF satellite attitude sensors is not always adequate to correctly point the UVPI cameras. Our solution is to point the UVPI cameras at known targets and use the information thus gained to improve attitude measurements. This paper describes the three methods developed to determine improved attitude values using the UVPI for both real-time operations and post observation analysis.

Miglin, M. F.↗
NASA NTRS1993

Attitude control of the LACE satellite: A gravity gradient stabilized spacecraft

The Low-power Atmospheric Compensation Experiment (LACE) satellite was launched in February 1990 by the Naval Research Laboratory. The spacecraft's pitch and roll are maintained with a gravity gradient boom and a magnetic damper. There are two other booms with much smaller tip masses, one in the velocity direction (lead boom) of variable length and the other in the opposite direction (balance boom) also of variable length. In addition, the system uses a momentum wheel with its axis perpendicular to the plane of the orbit to control yaw and keep these booms in the orbital plane. The primary LACE experiment requires that the lead boom be moved to lengths varying from 4.6 m to 45.7 m. This and other onboard experiments require that the spacecraft attitude remain within tight constraints while operating. The problem confronting the satellite operators was to move the lead boom without inducing a net spacecraft attitude disturbance. A description of a method used to change the length of the lead boom while minimizing the disturbance to the attitude of the spacecraft is given. Deadbeating to dampen pitch oscillations has also been accomplished by maneuvering either the lead or balance boom and is discussed.

Ivory, J. E.↗
NASA NTRS2018

The Lunar Neon Exosphere Seen in LACE Data

Using the LACE data from Apollo 17 we have found measured neon densities consistent with the 20Ne surface number densities reported by Cook et al. (2013) for normal conditions, terminator surface densities of 3 (±1.5) × 10(exp 3) per cu.cm. These values are almost an order of magnitude less than those reported by Benna et al. (2015) for CME conditions. Using a Monte Carlo model and assuming the normal solar wind and a photoionization lifetime for Ne of 300 days, our result was more consistent with the Benna (2015) result than our measured result. Two lunations showed an increase in Ne during the night, consistent with the simulation, but two of the lunations showed a decrease in surface number density through the night. We have shown that explaining the Ne distribution is not as simple as assuming dynamic equilibrium with the solar wind and an exosphere accommodated to the local surface temperature.

LACE Data↗
NASA NTRS1966

Tool pre-tensions covers prior to lacing

In securing a bulky object in a storage compartment, a cinching or tightening tool is used to draw two opposing cover halves together at a predetermined tension to permit quick lacing to retain the stored object. This tool is also useful in fabrication industries to draw components together during assembly or treating.

Forman, M. A.↗
NASA NTRS1979

The Look-point Aircraft Coordinate Estimator (LACE) and potential applications

A look-point aircraft coordinate estimator (LACE) consisting of a windshield runway symbol projector, pilot input controls, microprocessor, and eye-alignment device is described. The estimator is used by a pilot to determine his aircraft's position relative to a runway or other visible terrain or target. The pilot initially superimposes and then corrects the superposition of the runway symbol over the runway during approach during periods when the runway is visible. Using the pilot's inputs the microprocessor calculates the position of the aircraft in terms of runway coordinates, then generates an approach trajectory and issues instructions to an autopilot. The microprocessor contains a model of the aircraft's dynamics and calculates a theoretical aircraft trajectory. The theoretical position of the aircraft is then used to drive the runway symbol, with the pilot's input being additive. The system thus acts as an aid in making low visibility approaches and landings when only an occasional glimpse of the runway is possible and no ground referenced landing systems are available. The system can also be used as an independent landing monitor for ground referenced landing systems.

Anderson, W. W.↗
DOE OSTI2020

Materials Data on LaCe(SiPd)4 by Materials Project

CeLa(PdSi)4 crystallizes in the tetragonal P4/mmm space group. The structure is three-dimensional. Ce3+ is bonded to eight equivalent Si4- atoms to form CeSi8 hexagonal bipyramids that share corners with sixteen equivalent PdSi4 tetrahedra, edges with four equivalent CeSi8 hexagonal bipyramids, edges with eight equivalent PdSi4 tetrahedra, and faces with four equivalent CeSi8 hexagonal bipyramids. All Ce–Si bond lengths are 3.22 Å. La3+ is bonded to eight equivalent Si4- atoms to form LaSi8 hexagonal bipyramids that share corners with sixteen equivalent PdSi4 tetrahedra, edges with four equivalent LaSi8 hexagonal bipyramids, edges with eight equivalent PdSi4 tetrahedra, and faces with four equivalent LaSi8 hexagonal bipyramids. All La–Si bond lengths are 3.23 Å. Pd+2.50+ is bonded to four Si4- atoms to form PdSi4 tetrahedra that share corners with four equivalent CeSi8 hexagonal bipyramids, corners with four equivalent LaSi8 hexagonal bipyramids, corners with four equivalent PdSi4 tetrahedra, edges with two equivalent CeSi8 hexagonal bipyramids, edges with two equivalent LaSi8 hexagonal bipyramids, and edges with four equivalent PdSi4 tetrahedra. There are two shorter (2.49 Å) and two longer (2.50 Å) Pd–Si bond lengths. There are two inequivalent Si4- sites. In the first Si4- site, Si4- is bonded in a 9-coordinate geometry to four equivalent Ce3+, four equivalent Pd+2.50+, and one Si4- atom. The Si–Si bond length is 2.34 Å. In the second Si4- site, Si4- is bonded in a 9-coordinate geometry to four equivalent La3+, four equivalent Pd+2.50+, and one Si4- atom. The Si–Si bond length is 2.39 Å.

36 MATERIALS SCIENCE↗
DOE OSTI2020

Materials Data on LaCe(MnSi)4 by Materials Project

CeLa(MnSi)4 crystallizes in the tetragonal P4/mmm space group. The structure is three-dimensional. Ce3+ is bonded in a body-centered cubic geometry to eight equivalent Si4- atoms. All Ce–Si bond lengths are 3.09 Å. La3+ is bonded in a body-centered cubic geometry to eight equivalent Si4- atoms. All La–Si bond lengths are 3.12 Å. Mn+2.50+ is bonded to four Si4- atoms to form a mixture of edge and corner-sharing MnSi4 tetrahedra. There are two shorter (2.38 Å) and two longer (2.39 Å) Mn–Si bond lengths. There are two inequivalent Si4- sites. In the first Si4- site, Si4- is bonded in a 9-coordinate geometry to four equivalent Ce3+, four equivalent Mn+2.50+, and one Si4- atom. The Si–Si bond length is 2.55 Å. In the second Si4- site, Si4- is bonded in a 9-coordinate geometry to four equivalent La3+, four equivalent Mn+2.50+, and one Si4- atom. The Si–Si bond length is 2.72 Å.

36 MATERIALS SCIENCE↗
DOE OSTI2020

Materials Data on LaCe(GePt)4 by Materials Project

CeLa(PtGe)4 crystallizes in the triclinic P1 space group. The structure is three-dimensional. Ce is bonded in a 12-coordinate geometry to eight Pt and eight Ge atoms. There are a spread of Ce–Pt bond distances ranging from 3.29–3.40 Å. There are a spread of Ce–Ge bond distances ranging from 3.25–3.40 Å. La is bonded in a 8-coordinate geometry to eight Pt and eight Ge atoms. There are a spread of La–Pt bond distances ranging from 3.33–3.42 Å. There are a spread of La–Ge bond distances ranging from 3.30–3.39 Å. There are four inequivalent Pt sites. In the first Pt site, Pt is bonded in a 5-coordinate geometry to four equivalent La and five Ge atoms. There are a spread of Pt–Ge bond distances ranging from 2.49–2.54 Å. In the second Pt site, Pt is bonded in a 9-coordinate geometry to four equivalent Ce and five Ge atoms. There are a spread of Pt–Ge bond distances ranging from 2.45–2.53 Å. In the third Pt site, Pt is bonded in a 4-coordinate geometry to two equivalent Ce, two equivalent La, and four Ge atoms. There are a spread of Pt–Ge bond distances ranging from 2.54–2.60 Å. In the fourth Pt site, Pt is bonded in a 4-coordinate geometry to two equivalent Ce, two equivalent La, and four Ge atoms. There are a spread of Pt–Ge bond distances ranging from 2.54–2.58 Å. There are four inequivalent Ge sites. In the first Ge site, Ge is bonded in a 4-coordinate geometry to two equivalent Ce, two equivalent La, and four Pt atoms. In the second Ge site, Ge is bonded in a 4-coordinate geometry to two equivalent Ce, two equivalent La, and four Pt atoms. In the third Ge site, Ge is bonded in a 9-coordinate geometry to four equivalent La and five Pt atoms. In the fourth Ge site, Ge is bonded in a 9-coordinate geometry to four equivalent Ce and five Pt atoms.

36 MATERIALS SCIENCE↗
DOE OSTI2020

Materials Data on LaCe(CuSi)4 by Materials Project

CeLa(CuSi)4 crystallizes in the tetragonal P4/mmm space group. The structure is three-dimensional. Ce4+ is bonded to eight equivalent Si4- atoms to form CeSi8 hexagonal bipyramids that share corners with sixteen equivalent CuSi4 tetrahedra, edges with four equivalent CeSi8 hexagonal bipyramids, edges with eight equivalent CuSi4 tetrahedra, and faces with four equivalent CeSi8 hexagonal bipyramids. All Ce–Si bond lengths are 3.14 Å. La3+ is bonded in a distorted body-centered cubic geometry to eight equivalent Si4- atoms. All La–Si bond lengths are 3.15 Å. Cu+2.25+ is bonded to four Si4- atoms to form CuSi4 tetrahedra that share corners with four equivalent CeSi8 hexagonal bipyramids, corners with four equivalent CuSi4 tetrahedra, edges with two equivalent CeSi8 hexagonal bipyramids, and edges with four equivalent CuSi4 tetrahedra. There are two shorter (2.41 Å) and two longer (2.42 Å) Cu–Si bond lengths. There are two inequivalent Si4- sites. In the first Si4- site, Si4- is bonded in a 9-coordinate geometry to four equivalent Ce4+, four equivalent Cu+2.25+, and one Si4- atom. The Si–Si bond length is 2.37 Å. In the second Si4- site, Si4- is bonded in a 9-coordinate geometry to four equivalent La3+, four equivalent Cu+2.25+, and one Si4- atom. The Si–Si bond length is 2.44 Å.

36 MATERIALS SCIENCE↗
DOE OSTI2020

Materials Data on LaCe by Materials Project

CeLa is alpha La-derived structured and crystallizes in the trigonal R-3m space group. The structure is three-dimensional. there are three inequivalent Ce sites. In the first Ce site, Ce is bonded to six equivalent Ce and six equivalent La atoms to form CeLa6Ce6 cuboctahedra that share corners with twelve CeLa6Ce6 cuboctahedra, edges with twelve CeLa6Ce6 cuboctahedra, edges with twelve equivalent LaLa6Ce6 cuboctahedra, faces with six equivalent CeLa6Ce6 cuboctahedra, and faces with twelve equivalent LaLa6Ce6 cuboctahedra. All Ce–Ce bond lengths are 3.55 Å. All Ce–La bond lengths are 3.59 Å. In the second Ce site, Ce is bonded to six equivalent Ce and six La atoms to form CeLa6Ce6 cuboctahedra that share corners with five equivalent LaLa10Ce6 cuboctahedra, corners with twelve CeLa6Ce6 cuboctahedra, edges with ten LaLa6Ce6 cuboctahedra, edges with twelve CeLa6Ce6 cuboctahedra, faces with six equivalent CeLa6Ce6 cuboctahedra, and faces with fifteen LaLa6Ce6 cuboctahedra. All Ce–Ce bond lengths are 3.55 Å. All Ce–La bond lengths are 3.59 Å. In the third Ce site, Ce is bonded to six equivalent Ce and six La atoms to form CeLa6Ce6 cuboctahedra that share corners with five equivalent LaLa10Ce6 cuboctahedra, corners with twelve CeLa6Ce6 cuboctahedra, edges with ten LaLa6Ce6 cuboctahedra, edges with twelve CeLa6Ce6 cuboctahedra, faces with six equivalent CeLa6Ce6 cuboctahedra, and faces with fifteen LaLa6Ce6 cuboctahedra. All Ce–Ce bond lengths are 3.55 Å. All Ce–La bond lengths are 3.59 Å. There are two inequivalent La sites. In the first La site, La is bonded to six Ce and six equivalent La atoms to form LaLa6Ce6 cuboctahedra that share corners with twelve LaLa6Ce6 cuboctahedra, edges with twelve CeLa6Ce6 cuboctahedra, edges with twelve LaLa6Ce6 cuboctahedra, faces with six equivalent LaLa6Ce6 cuboctahedra, and faces with twelve CeLa6Ce6 cuboctahedra. All La–La bond lengths are 3.55 Å. In the second La site, La is bonded to six Ce and ten equivalent La atoms to form LaLa10Ce6 cuboctahedra that share corners with ten CeLa6Ce6 cuboctahedra, corners with twelve LaLa6Ce6 cuboctahedra, edges with eight CeLa6Ce6 cuboctahedra, edges with sixteen LaLa6Ce6 cuboctahedra, faces with sixteen equivalent LaLa10Ce6 cuboctahedra, and faces with eighteen CeLa6Ce6 cuboctahedra. There are a spread of La–La bond distances ranging from 3.55–7.11 Å.

36 MATERIALS SCIENCE↗
DOE OSTI2024

Red–green–blue Boolean image analysis of particulate debris laced with luminescent tracers

Abstract Particulate mass estimation from 3-pixel images is desirable in many fields. Red–green–blue (RGB) analysis and Boolean logic were shown to estimate the mass of luminescent tracers in microscopic images. With a controlled background intensity, an estimation error of 1.8 to 3.5% was achieved; in uncontrolled backgrounds, an error of about 18% was achieved. RGB analysis is a valuable tool for spatial location of particulates. This work shows it is possible to estimate the particulate mass in an image and gives RGB an extension into mass quantification that has far-reaching impacts in fields involving the fate and transport of particulate matter. Graphical abstract

36 MATERIALS SCIENCE↗
NASA NTRS2012

Organizational Influences on Interdisciplinary Interactions during Research and Design of Large-Scale Complex Engineered Systems

The design of large-scale complex engineered systems (LaCES) such as an aircraft is inherently interdisciplinary. Multiple engineering disciplines, drawing from a team of hundreds to thousands of engineers and scientists, are woven together throughout the research, development, and systems engineering processes to realize one system. Though research and development (R&D) is typically focused in single disciplines, the interdependencies involved in LaCES require interdisciplinary R&D efforts. This study investigates the interdisciplinary interactions that take place during the R&D and early conceptual design phases in the design of LaCES. Our theoretical framework is informed by both engineering practices and social science research on complex organizations. This paper provides preliminary perspective on some of the organizational influences on interdisciplinary interactions based on organization theory (specifically sensemaking), data from a survey of LaCES experts, and the authors experience in the research and design. The analysis reveals couplings between the engineered system and the organization that creates it. Survey respondents noted the importance of interdisciplinary interactions and their significant benefit to the engineered system, such as innovation and problem mitigation. Substantial obstacles to interdisciplinarity are uncovered beyond engineering that include communication and organizational challenges. Addressing these challenges may ultimately foster greater efficiencies in the design and development of LaCES and improved system performance by assisting with the collective integration of interdependent knowledge bases early in the R&D effort. This research suggests that organizational and human dynamics heavily influence and even constrain the engineering effort for large-scale complex systems.

McGowan, Anna-Maria R.↗
NASA NTRS1993

CSI flight experiment projects of the Naval Research Laboratory

The Naval Research Laboratory (NRL) is involved in an active program of CSI flight experiments. The first CSI flight experiment of the Naval Research Laboratory, the Low Power Atmospheric Compensation Experiment (LACE) dynamics experiment, has successfully measured vibrations of an orbiting satellite with a ground-based laser radar. The observations, made on January 7, 8 and 10, 1991, represent the first ever measurements of this type. In the tests, a narrowband heterodyne CO2 laser radar, operating at a wavelength of 10.6 microns, detected vibration induced differential-Doppler signatures of the LACE satellite. Power spectral densities of forced oscillations and modal frequencies and damping rates of free-damped vibrations were obtained and compared with finite element structural models of the LACE system. Another manifested flight experiment is the Advanced Controls Technology Experiment (ACTEX) designed to demonstrate active and passive damping with piezo-electric (PZT) sensors and actuators. This experiment was developed under the management of the Air Force Phillips Laboratory with integration of the experiment at NRL. It is to ride as a secondary, or 'piggyback,' experiment on a future Navy satellite.

Fisher, Shalom↗