Quantitative evaluations of the structural loads, stiffness and deflections of an example Space Station truss due to a variety of influences, including manufacturing tolerances, assembly operations, and operational loading are reported. The example truss is a dual-keel design composed of 5-meter-cube modules. The truss is 21 modules high and 9 modules wide, with a transverse beam 15 modules long. One problem of concern is the amount of mismatch which will be expected when the truss is being...
Topics: NASA Technical Reports Server (NTRS), DYNAMIC STRUCTURAL ANALYSIS, LOADS (FORCES), ORBITAL...
The application of the Pactruss deployable structure to the support of large paraboloidal reflectors of very high precision was studied. The Pactruss concept, originally conceived for the Space Station truss, is shown to be suitable for use in a triangular arrangement to support a reflector surface composed of hexagonal reflector panels. A hybrid of Pactruss structural and deployable single-fold beams is shown to accommodate a center body. A minor alteration in the geometry is in order to avoid...
Topics: NASA Technical Reports Server (NTRS), BEAMS (SUPPORTS), DEPLOYMENT, HYBRID STRUCTURES, LARGE...
Extensible booms which could function as the diagonal spars and central mast of an 800 meter square, non-rotating Solar Sailing Vehicle were conceptually designed and analyzed. The boom design concept that was investigated is an extensible lattice boom which is stowed and deployed by elastically coiling and uncoiling its continuous longerons. The seven different free-span lengths in each spar which would minimize the total weights of the spars and mast were determined. Boom weights were...
Topics: NASA Technical Reports Server (NTRS), BOOMS (EQUIPMENT), DESIGN ANALYSIS, SOLAR SAILS, LONGERONS,...
Version 3.0 of the Solid Modeling Aerospace Research Tool (SMART Structures) is used to generate structural models for conceptual and preliminary-level aerospace designs. Features include the generation of structural elements for wings and fuselages, the integration of wing and fuselage structural assemblies, and the integration of fuselage and tail structural assemblies. The highly interactive nature of this software allows the structural engineer to move quickly from a geometry that defines a...
Topics: NASA Technical Reports Server (NTRS), USER MANUALS (COMPUTER PROGRAMS), COMPUTER PROGRAMS,...
Santek's ability to recover from a schedule slip was reviewed and found satisfactory. Diagonal member bond joints were subjected to static load to failure tests. Results are considered adequate.
Topics: NASA Technical Reports Server (NTRS), ASSEMBLING, CONTRACT MANAGEMENT, SPACE ERECTABLE STRUCTURES,...
A deployable M-braced truss structure, efficiently packaged into a compact stowed position and expandable to an operative position at the use site is described. The M-braced configuration effectively separates tension compression and shear in the structure and permits efficient structural design. Both diagonals and longerons telescope from an M-braced base unit and deploy either pneumatically, mechanically by springs or cables, or by powered reciprocating mechanisms. Upon full deployment, the...
Topics: NASA Technical Reports Server (NTRS), COMPRESSION LOADS, FOLDING STRUCTURES, STRUCTURAL STABILITY,...
Future in-space construction and assembly facilities will require the use of space cranes capable of supporting and manipulating large and massive loads. The large size of the space components being considered for construction will require that these cranes have a reach on the order of 100 meters. A space crane constructed from an erectable four-longeron truss beam with 19 5-sq-m truss bays is considered. This concept was selected to be compatible with the Space Station truss. This truss is...
Topics: NASA Technical Reports Server (NTRS), CRANES, ORBITAL ASSEMBLY, SPACE STATIONS, STATIC TESTS, BEAMS...
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255
Sep 20, 2010
09/10
by
Powers, Sheryll Goecke; Webb, Lannie D.; Friend, Edward L.; Lokos, William A
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The mission adaptive wing (MAW) consisted of leading- and trailing-edge variable-camber surfaces that could be deflected in flight to provide a near-ideal wing camber shape for any flight condition. These surfaces featured smooth, flexible upper surfaces and fully enclosed lower surfaces, distinguishing them from conventional flaps that have discontinuous surfaces and exposed or semiexposed mechanisms. Camber shape was controlled by either a manual or automatic flight control system. The wing...
Topics: AIRCRAFT STRUCTURES, AIRFRAMES, FUSELAGES, LONGERONS, OPENINGS, SPACING, COMPOSITE STRUCTURES, COST...
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155
May 31, 2011
05/11
by
Sauvageau, Donald R
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As part of the continuing effort to identify approaches to improve the safety and reliability of the Space Shuttle system, a Five-Segment Booster (FSB) design was conceptualized as a replacement for the current Space Shuttle boosters. The FSB offers a simple, unique approach to improve astronaut safety and increase performance margin. To determine the feasibility of the FSB, a Phase A study effort was sponsored by NASA and directed by the Marshall Space Flight Center. This study was initiated...
Topics: BOLTS, X-33 REUSABLE LAUNCH VEHICLE, DEBONDING (MATERIALS), DEFECTS, JOINTS (JUNCTIONS), SANDWICH...
Seven low cost multi-100 kW planar solar array modules were fabricated and tested. Two different designs were used, demonstrating advanced solar array construction practices. Both module types utilized second generation gridded back cells featuring high efficiency and IR transparency. A silicon dioxide AR coating optimized for transmission at gamma = 1.7 microns was applied to the back surface. Two interconnect types, a single sheet printed circuit and a roll type, with alternate approaches to...
Topics: NASA Technical Reports Server (NTRS), COST EFFECTIVENESS, COST REDUCTION, LARGE SPACE STRUCTURES,...
The structural design and configuration feasibility of the long spacer truss assembly that will be used as part of the Space Station Freedom is the focus of this study. The structural analysis discussed herein is derived from the transient loading events presented in the Space Transportation System Interface Control Document (STS ICD). The transient loading events are liftoff, landing, and emergency landing loads. Quasi-static loading events were neglected in this study since the magnitude of...
Topics: NASA Technical Reports Server (NTRS), SAFETY FACTORS, SPACE STATION STRUCTURES, SPACERS, STRUCTURAL...
The present invention is an intelligent flow control valve which may be inserted into the flow coming out of a pipe and activated to provide a method to stop, measure, and meter flow coming from the open or possibly broken pipe. The intelligent flow control valve may be used to stop the flow while repairs are made. Once repairs have been made, the valve may be removed or used as a control valve to meter the amount of flow from inside the pipe. With the addition of instrumentation, the valve may...
Topics: NASA Technical Reports Server (NTRS), PIPES (TUBES), CONTROL VALVES, FLOWMETERS, ANCHORS...
Exposure to solar radiation is one of the primary causes of degradation of materials on spacecraft. Accurate knowledge of solar exposure is needed to evaluate the performance of materials carried on the Long Duration Exposure Facility (LDEF) during its nearly 6 year orbital flight. Presented here are tables and figures of calculated solar exposure for the experiment rows, longerons, and end bays of the spacecraft as functions of time in orbit. The data covers both direct solar and earth...
Topics: NASA Technical Reports Server (NTRS), DEGRADATION, EXPOSURE, IRRADIANCE, LONG DURATION EXPOSURE...
Atomic oxygen exposures were determined analytically for rows, longerons, and end bays of the Long Duration Exposure Facility (LDEF). The calculations are based on an analytical model that accounts for the effects of thermal molecular velocity, atmospheric temperature, number density, spacecraft velocity, incidence angle, and atmospheric rotation on atomic oxygen flux. Results incorporate variations in solar activity, geomagnetic index, and orbital parameters occurring over the 6-year flight of...
Topics: NASA Technical Reports Server (NTRS), EARTH ORBITAL ENVIRONMENTS, ENVIRONMENTAL TESTS, EXPOSURE,...
A program was conducted to develop the technology for joints and cutouts in a composite fuselage that meets all design requirements of a large transport aircraft for the 1990s. An advanced trijet derivative of the DC-10 was selected as the baseline aircraft. Design and analysis of a 30-foot-long composite fuselage barrel provided a realistic basis for the test effort. The primary composite material was Hexcel F584 resin on 12 K IM6 fiber, in tape and broadgoods form. Fiberglass broadgoods were...
Topics: NASA Technical Reports Server (NTRS), AIRCRAFT CONSTRUCTION MATERIALS, AIRCRAFT DESIGN, FIBER...
A hybrid spar of titanium with an integrally brazed composite, consisting of an aluminum matrix reinforced with boron-carbide-coated fibers, was heated in an oven and the resulting thermal stresses were measured. Uniform heating of the spar in an oven resulted in thermal stresses arising from the effects of dissimilar materials and anisotropy of the metal matrix composite. Thermal stresses were calculated from a finite element structural model using anisotropic material properties deduced from...
Topics: NASA Technical Reports Server (NTRS), FINITE ELEMENT METHOD, LONGERONS, MATRIX METHODS, THERMAL...
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307
Jul 23, 2010
07/10
by
Brinker, David J.; Weinberg, Irvin
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Recent developments and progress in indium phosphide solar cell research for space application are reviewed. Indium phosphide homojunction cells were fabricated in both the np and pn configurations with total area efficiencies of 17.9 and 15.9 (air mass 0 and 25 C) respectively. Organometallic chemical vapor deposition, liquid phase epitaxy, ion implantation and diffusion techniques were employed in InP cell fabrication. A theoretical model of a radiation tolerant, high efficiency homojunction...
Topics: BAYS (STRUCTURAL UNITS), EXPANDABLE STRUCTURES, FOLDING STRUCTURES, LARGE SPACE STRUCTURES,...
Control theory and design, dynamic system modelling, and simulation of test scenarios are the main ideas discussed. The overall effort is the achievement at Marshall Space Flight Center of a successful ground test experiment of a large space structure. A simplified planar model of ground test experiment of a large space structure. A simplified planar model of ground test verification was developed. The elimination from that model of the uncontrollable rigid body modes was also examined. Also...
Topics: NASA Technical Reports Server (NTRS), CONTROL THEORY, EXPERIMENT DESIGN, GROUND TESTS, LARGE SPACE...
The composite liquid hydrogen tank (tank #1 of 2) for the X-33 flight vehicle is made up of four lobes that have a sandwich construction, bonded to a frame of longerons. Lobes 1 and 4 showed local disbonds to the longerons they were bonded to. The 'bad' areas were cut away and patched with new material. The new material was cured by placing the entire tank in a heated autoclave with no pressure. Upon removal from the autoclave, it was noted that lobe 1 had severe skin/core disbonds on the inner...
Topics: NASA Technical Reports Server (NTRS), BOLTS, DEBONDING (MATERIALS), DEFECTS, JOINTS (JUNCTIONS),...
A prototype deployer for the STACBEAM (Stacking Triangular Articulated Compact Beam) is being developed. The STACBEAM is an accordian-folded solar array blanket. The prototype was constructed as a point design for support of a 23.9-kW blanket and is described.
Topics: NASA Technical Reports Server (NTRS), GEOSYNCHRONOUS ORBITS, LONGERONS, SOLAR ARRAYS, SPACECRAFT...
Directions regarding the analytical models were received. A counter balance arm with weights was added at the top of the ASTROMAST to offset the arm with the gimbals. In addition to this model, three more models were requested from MSFC: structure as in the revised model with the addition of lumped masses at bays 46 and 91 of the ASTROMAST; cantilevered cruciform structure with lumped masses at bays 46 and 91, and an all up cruciform structure with lumped masses at bays 46 and 91. Figures for...
Topics: NASA Technical Reports Server (NTRS), CONTROL SYSTEMS DESIGN, LARGE SPACE STRUCTURES, LONGERONS,...
In January 2007, the NASA Administrator and Associate Administrator for the Exploration Systems Mission Directorate chartered the NASA Engineering and Safety Center (NESC) to design, build, and test a full-scale Composite Crew Module (CCM). For the design and manufacturing of the CCM, the team adopted the building block approach where design and manufacturing risks were mitigated through manufacturing trials and structural testing at various levels of complexity. Following NASA's Structural...
Topics: NASA Technical Reports Server (NTRS), SPACECRAFT MODULES, FULL SCALE TESTS, HONEYCOMB CORES,...
The design of deployable structures involves a complicated tradeoff of packaging efficiency, the overall mechanism associated with deploying and latching beam joints, and the requirements and complexity of the beam deployer/repacker. Three longeron deployable beams, controllable geometry beams, and hybrid deployable/erectable beam concepts are evaluated.
Topics: NASA Technical Reports Server (NTRS), BEAMS, DEPLOYMENT, LARGE SPACE STRUCTURES, SPACE ERECTABLE...
Three space crane articulated truss joint concepts are studied to evaluate their static structural performance over a range of geometric design parameters. Emphasis is placed on maintaining the four longeron reference truss performance across the joint while allowing large angle articulation. A maximum positive articulation angle and the actuator length ratio required to reach the angle are computed for each concept as the design parameters are varied. Configurations with a maximum articulation...
Topics: NASA Technical Reports Server (NTRS), CRANES, DESIGN ANALYSIS, MATHEMATICAL MODELS, ORBITAL...
The International Space Station s solar array wing mast shadowing problem is the focus of this paper. A building-block approach to modeling and analysis is pursued for the primary structural components of the solar array wing mast structure. Starting with an ANSYS (Registered Trademark) finite element model, a verified MSC.Nastran (Trademark) model is established for a single longeron. This finite element model translation requires the conversion of several modeling and analysis features for...
Topics: NASA Technical Reports Server (NTRS), INTERNATIONAL SPACE STATION, SOLAR ARRAYS, STRUCTURAL...
The Galileo spacecraft utilizes a deployable lattice boom to position three science instruments at remote distances from the spacecraft body. An improved structure and mechanism to precisely control deployment of the boom, and the unique deployment of an outer protective cover are described.
Topics: NASA Technical Reports Server (NTRS), BOOMS (EQUIPMENT), DEPLOYMENT, GALILEO SPACECRAFT,...
A spinning Earth satellite is shown in which it is desired to reduce the rotation or spin to a level that the satellite may be secured or handled remotely from a spacecraft. This is accomplished by the spacecraft having a mast carrying an electrical current coil which encircles the satellite. The magnetic field of the coil is normal to the spin axis of the satellite which causes circular eddy current flow in the housing of the satellite. This generates magnetic force opposing the rotation. In...
Topics: NASA Technical Reports Server (NTRS), CONTROL EQUIPMENT, ELECTRIC CURRENT, ELECTROMAGNETS,...
A deployable geodesic truss structure which can be deployed from a stowed state to an erected state is described. The truss structure includes a series of bays, each bay having sets of battens connected by longitudinal cross members which give the bay its axial and torsional stiffness. The cross members are hinged at their mid point by a joint so that the cross members are foldable for deployment or collapsing. The bays are deployed and stabilized by actuator means connected between the mid...
Topics: NASA Technical Reports Server (NTRS), BAYS (STRUCTURAL UNITS), EXPANDABLE STRUCTURES, FOLDING...
Extension of antennas and thrust modules from the primary structure of the space station will require deployable beams of high stiffness and strength, as well as low mass and package volume. A square boom cross section is desirable for interface reasons. These requirements and others are satisfied by the X-beam. The X-beam folds by simple geometry, using single-degree-of-freedom hinges at simple angles, with no strain during deployment. Strut members are of large diameter with unidirectional...
Topics: NASA Technical Reports Server (NTRS), BEAMS (SUPPORTS), FOLDING STRUCTURES, LONGERONS, RETRACTABLE...
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1.0K
May 22, 2011
05/11
by
Campbell, Frank J
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The Navy is experiencing a severe aircraft electrical wiring maintenance problem as a result of the extensive use of an aromatic polyimide insulation that is deteriorating at a rate that was unexpected when this wire was initially selected. This problem has significantly affected readiness, reliability, and safety and has greatly increased the cost of ownership of Naval aircraft. Failures in wire harnesses have exhibited arcing and burning that will propagate drastically, to the interruption of...
Topics: BEAMS (SUPPORTS), JOINTS (JUNCTIONS), SPACE ERECTABLE STRUCTURES, TRUSSES, AXES OF ROTATION,...
Four cracked longerons, containing a total of eight cracks, were provided for study. Cracked regions were cut from the longerons. Load was applied to open the cracks, enabling crack surface examination. Examination revealed that crack propagation was driven by fatigue loading in all eight cases. Fatigue crack initiation appears to have occurred on the top edge of the longerons near geometric changes that affect component bending stiffness. Additionally, metallurgical analysis has revealed a...
Topics: NASA Technical Reports Server (NTRS), CRACK INITIATION, LONGERONS, HELICOPTERS, SURFACE CRACKS,...
The ground test article fabrication and assembly plan was completed by Santek Engineering, Inc. The plan was reviewed and accepted by Rockwell during an on-site visit to the Santek facility. Raw material and hardware orders were placed by Santek in July. Approximately 98% of the raw materials and 10% of the hardware deliveries have been completed. Several material and hardware substitutions were requested by Santek due to no-bid responses from suppliers or excessive costs for limited quantity...
Topics: NASA Technical Reports Server (NTRS), DEPLOYMENT, FOLDING STRUCTURES, LARGE SPACE STRUCTURES,...
A column longeron latch assembly provides the securing mechanism for the deployable, telescoping column of a hoop/column antenna. The column is an open lattice structure with three longerons disposed 120 deg apart as the principle load bearing member. The column is deployed from a pair of eleven nested bays disposed on opposite sides of a center section under the influence of a motor-cable-pulley system. The longeron latch is a four bar linkage mechanism using the over-center principle for...
Topics: NASA Technical Reports Server (NTRS), DEPLOYMENT, HOOP COLUMN ANTENNAS, LARGE SPACE STRUCTURES,...
A study is presented of the development of the Remote Manipulator System (RMS) configurations for jettison of the solar panels on the Solar Maximum Mission/Multimission Satellite. A valid RMS maneuver between jettison configurations was developed. Arm and longeron loads and effector excursions due to the solar panel jettison were determined to see if they were within acceptable limits. These loads and end effector excursions were analyzed under two RMS modes, servos active in position hold...
Topics: NASA Technical Reports Server (NTRS), JETTISON SYSTEMS, REMOTE MANIPULATOR SYSTEM, SOLAR ARRAYS,...
The methodology used to assess the probability of no impact of space debris and meteoroids on a spacecraft structure is applied to the Space Station solar array assembly. Starting with the space debris and meteoroids flux models, the projected surface area of the solar cell string circuit of the solar array panel and the mast longeron, and the design lifetime, the possibility of no impact on the solar array mast and solar cell string circuits was determined as a function of particle size. The...
Topics: NASA Technical Reports Server (NTRS), IMPACT DAMAGE, METEOROID HAZARDS, MICROMETEOROIDS, SOLAR...
The Column Longeron Latch (CLL) was designed and developed as the securing mechanism for the deployable, telescoping column of the Hoop/Column antenna. The column is an open lattice structure with three longerons as the principal load-bearing members. It is divided into telescoping sections that are deployed after the antenna is place in Earth orbit. The CLL provides a means to automatically lock the longeron sections into position during deployment as well as a means of unlocking the sections...
Topics: NASA Technical Reports Server (NTRS), ANTENNAS, FOLDING STRUCTURES, LARGE SPACE STRUCTURES,...
The orbiter cargo bay thermal environment data is presented. Measurements include: insulation surface temperatures, wire tray surface temperatures, sill longeron temperatures, gas temperatures, radiator temperatures, and gas pressure.
Topics: NASA Technical Reports Server (NTRS), ENVIRONMENTAL MONITORING, PAYLOAD STATIONS, SPACE SHUTTLES,...
Coilable-longeron lattice columns called Astromasts (trademark) were manufactured for a variety of spacecraft missions. These flight structures varied in diameter from 0.2 to 0.5 meter (9 to 19 in.), and the longest Astromast of this type deploys to a length of 30 meters (100 feet). A double-laced diagonal Astromast design referred to as the Supermast (trademark) which, because it has shorter baylengths than an Astromast, is approximately four times as strong. The longeron cross section and...
Topics: NASA Technical Reports Server (NTRS), LONGERONS, SPACE MISSIONS, SPACECRAFT COMPONENTS, CROSS...
A tetrahedral beam that can be compactly stowed, sequentially deployed, and widely manipulated to provide a structurally sound yet highly maneuverable truss structure is comprised of a number of repeating units of tandem tetralhedral sharing common sides. Fixed length battens are jointed into equilateral triangles called batten frames. Apexes of adjacent triangles are interconnected by longerons having a mid-point folding hinge. Joints, comprised of gussets pivotabley connected by links, permit...
Topics: NASA Technical Reports Server (NTRS), BEAMS (SUPPORTS), DEPLOYMENT, FOLDING STRUCTURES,...
On December 9th 2009, the International Space Station (ISS) 2A solar array mast experienced prolonged longeron shadowing during a Soyuz undocking. Analytical reconstruction of induced thermal and dynamic structural loads showed an exceedance of the mast buckling limit. Possible structural damage to the solar array mast could have occurred during this event. A Low fidelity video survey of the 2A mast showed no obvious damage of the mast longerons or battens. The decision was made to conduct an...
Topics: NASA Technical Reports Server (NTRS), INTERNATIONAL SPACE STATION, DYNAMIC STRUCTURAL ANALYSIS,...
