A tank and intertank sizing tool that includes effects of major design drivers, and which allows parametric studies to be performed, has been developed and calibrated against independent representative results. Although additional design features, such as bulkheads and field joints, are not currently included in the process, the improved level of fidelity has allowed parametric studies to be performed which have resulted in understanding of key tank and intertank design drivers, design...
Topics: NASA Technical Reports Server (NTRS), REUSABLE LAUNCH VEHICLES, RECOVERABLE LAUNCH VEHICLES, X-33...
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Jun 9, 2011
06/11
by
Shah, Gautam H.; Granda, J. Nije
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A brief overview of a cooperative NASA/Boeing research effort, Strake Technology Research Application to Transport Aircraft (STRATA), intended to explore the potential of applying forebody strake technology to transport aircraft configurations for directional stability and control at low angles of attack, is presented. As an initial step in the STRATA program, an exploratory wind-tunnel investigation of the effect of fixed forebody strakes on the directional stability and control...
Topics: AEROTHERMODYNAMICS, X-38 CREW RETURN VEHICLE, HYPERSONIC SPEED, RELIABILITY, REYNOLDS NUMBER,...
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May 28, 2011
05/11
by
Mackall, Dale; McBride, David; Cohen, Dorothe
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The Integrated Test Facility (ITF), being built at the NASA Ames Research Center's Dryden Flight Research Facility (ADFRF), will provide new real-time test capabilities for emerging research aircraft. An overview of the ITF and the real-time systems being developed to operate this unique facility are outlined in this paper. The ITF will reduce flight test risk by minimizing the difference between the flight- and ground-test environments. The ground-test environment is provided by combining...
Topics: SPACECRAFT LAUNCHING, DATA ACQUISITION, ROCKET NOZZLES, X-33 REUSABLE LAUNCH VEHICLE, BASE HEATING,...
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May 31, 2011
05/11
by
Booth, Earl R., Jr.; Wilbur, Matthew L
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The use of an Active Twist Rotor system to provide both vibration reduction and performance enhancement has been explored in recent analytical and experimental studies. Effects of active-twist control on rotor noise, however, had not been determined. During a recent wind tunnel test of an active-twist rotor system, a set of acoustic measurements were obtained to assess the effects of active-twist control on noise produced by the rotor, especially blade-vortex interaction (BVI) noise. It was...
Topics: REUSABLE LAUNCH VEHICLES, X-33 REUSABLE LAUNCH VEHICLE, AEROSPACE SAFETY, MONTE CARLO METHOD,...
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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...
Up until now, loads analyses of the X-33 RLV have been done at Marshall Space Flight Center (MSFC) using aerodynamic loads derived from CFD and wind tunnel models of a rigid vehicle. Control forces and moments are determined using a rigid vehicle trajectory analysis and the detailed control load distributions for achieving the desired control forces and moments, again on the rigid vehicle, are determined by Lockheed Martin Skunk Works. However, static aeroelastic effects upon the load...
Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC LOADS, AEROELASTICITY, STABILITY DERIVATIVES,...
Lockheed Martin Space Systems Company recently completed a two-year fabrication and test program on subscale composite liquid oxygen (LO2) tanks. The goals of this program included the development of fabrication and inspection techniques, cryogenic acceptance testing of composite articles, and demonstrating oxygen compatibility under launch vibration loads. Two subscale diameter test bottles were fabricated using a proprietary Lockheed Martin material, known as LM21C03. The bottles were then...
Topics: NASA Technical Reports Server (NTRS), AEROSPACE SYSTEMS, PRODUCT DEVELOPMENT, COMPOSITE...
X-33 is an advanced technology demonstrator vehicle for the Reusable Launch Vehicle (RLV) program. The thermal protection system (TPS) for the X-33 is composed of complex layers of materials to protect internal components, while withstanding severe external temperatures induced by aerodynamic heating during high speed flight. It also serves as the vehicle aeroshell in some regions using a stand-off design. MSC/NASTRAN thermal analysis capability was used to predict transient temperature...
Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC HEATING, CONDUCTIVE HEAT TRANSFER, INSULATION,...
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May 29, 2011
05/11
by
Scambos, Ted A
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This paper presents a final report on Variable Ice-Sheet Discharge and Coastal Change in West Antarctica. Results are given for Ice Shelf Patrol and Outlet glacier velocity mapping.
Topics: DESIGN ANALYSIS, PRODUCTION COSTS, LOW COST, VENTURESTAR LAUNCH VEHICLE, COMMERCIAL SPACECRAFT,...
From the first Saturn V rocket booster (S-II-T) testing in 1966 and the routine Space Shuttle Main Engine (SSME) testing beginning in 1975, to more recent test programs such as the X-33 Aerospike Engine, the Integrated Powerhead Development (IPD) program, and the Hybrid Sounding Rocket (HYSR), Stennis Space Center (SSC) continues to be a premier location for conducting large-scale propulsion testing. Central to each test program is the capability for sensor systems to deliver reliable...
Topics: NASA Technical Reports Server (NTRS), WIRELESS COMMUNICATION, SENSORS, SPACECRAFT PROPULSION,...
The X-33, NASA's flagship for reusable space plane technology demonstration, is on course to permit a crucial decision for the nation by the end of this decade. Lockheed Martin Skunk Works, NASA's partner in this effort, has led a dedicated and talented industry and government team that have met and solved numerous challenges within the first 26 months. This program began by accepting the mandate that included two unprecedented and highly challenging goals: 1) demonstrate single stage to orbit...
Topics: NASA Technical Reports Server (NTRS), TECHNOLOGY ASSESSMENT, X-33 REUSABLE LAUNCH VEHICLE,...
The VentureStar reusable launch vehicle is discussed in this viewgraph presentation. The objectives of the VentureStar program are reviewed: (1) expendables cost too much, (2) commercial space market is growing (3) meets NASA's goals, (4) Users want fast ground turnaround, (5) users want quick access to space, (6) the offline payload processing saves time, (7) low cost access to space will enable new markets. Flight tests of the X-33, which was designed to test the technology and is pictured in...
Topics: NASA Technical Reports Server (NTRS), FLIGHT TESTS, LOW COST, PAYLOADS, REUSABLE LAUNCH VEHICLES,...
Aeroheating characteristics of the X-33 Rev-F configuration have been experimentally examined in the Langley 20-Inch Mach 6 Air Tunnel (Test 6770). Global surface heat transfer distributions, surface streamline patterns, and shock shapes were measured on a 0.013-scale model at Mach 6 in air. Parametric variations include angles-of-attack of 20-deg, 30-deg, and 40-deg; Reynolds numbers based on model length of 0.9 to 4.9 million; and body-flap deflections of 10-deg and 20-deg. The effects of...
Topics: NASA Technical Reports Server (NTRS), X-33 REUSABLE LAUNCH VEHICLE, AERODYNAMIC HEATING,...
The Primary activities of Lee & Associates for the referenced Purchase Order has been in direct support of the X-33/Reusable Launch Vehicle Technology Program. An independent review to evaluate the X-33 liquid hydrogen fuel tank failure, which recently occurred after-test of the starboard tank has been provided. The purpose of the Investigation team was to assess the tank design modifications, provide an assessment of the testing approach used by MSFC (Marshall Space Flight Center) in...
Topics: NASA Technical Reports Server (NTRS), X-33 REUSABLE LAUNCH VEHICLE, FUEL TANKS, TECHNOLOGY...
Polymer Matrix Composite (PMC) hydrogen tanks have been proposed as an enabling technology for reducing the weight of Single-Stage-to-Orbit reusable launch vehicles where structural mass has a large impact on vehicle performance. A key development issue of these lightweight structures is the leakage of hydrogen through the composite material. The rate of hydrogen leakage can be a function of the material used, method of 6 fabrication used to manufacture the tank, mechanical load the tank must...
Topics: NASA Technical Reports Server (NTRS), POLYMER MATRIX COMPOSITES, LEAKAGE, PROPELLANT TANKS,...
Aerospace vehicles are designed to be durable and damage tolerant. Durability is largely an economic life-cycle design consideration whereas damage tolerance directly addresses the structural airworthiness (safety) of the vehicle. However, both durability and damage tolerance design methodologies must address the deleterious effects of changes in material properties and the initiation and growth of microstructural damage that may occur during the service lifetime of the vehicle. Durability and...
Topics: NASA Technical Reports Server (NTRS), AIRCRAFT RELIABILITY, DAMAGE, DESIGN ANALYSIS,...
As part of the overall goal of developing Integrated Vehicle Health Management (IVHM) systems for aerospace vehicles, NASA has focused considerable resources on the development of technologies for Structural Health Management (SHM). The motivations for these efforts are to increase the safety and reliability of aerospace structural systems, while at the same time decreasing operating and maintenance costs. Research and development of SHM technologies has been supported under a variety of...
Topics: NASA Technical Reports Server (NTRS), AEROSPACE VEHICLES, SYSTEMS HEALTH MONITORING, SYSTEMS...
The X-33 vehicle is an advanced technology demonstrator sponsored by NASA. For the past three years the Structural Dynamics & Loads Group of NASA's Marshall Space Flight Center has had the task of integrating the X-33 vehicle structural finite element model. In that time, five versions of the integrated vehicle model have been produced and a strategy has evolved that would benefit anyone given the task of integrating structural finite element models that have been generated by various...
Topics: NASA Technical Reports Server (NTRS), STRATEGY, FINITE ELEMENT METHOD, MODELS, X-33 REUSABLE LAUNCH...
This report documents the results of a study conducted to compute the inviscid longitudinal aerodynamic characteristics of a simplified X-33 configuration. The major components of the X-33 vehicle, namely the body, the canted fin, the vertical fin, and the body-flap, were simulated in the CFD (Computational Fluid Dynamic) model. The rear-ward facing surfaces at the base including the aerospike engine surfaces were not simulated. The FELISA software package consisting of an unstructured surface...
Topics: NASA Technical Reports Server (NTRS), COMPUTATIONAL FLUID DYNAMICS, INVISCID FLOW, VISCOUS FLOW,...
This viewgraph presentation gives an overview of the X-33 LH2 tank failure investigation findings. The conclusions of the investigation include the following: (1) the inner skin microcracked and hydrogen infiltrated; (2) the cracks grew larger under pressure; (3) when pressure was removed, the cracks closed slightly; (4) when the tank was drained and warmed, the cracks closed and blocked the leak path; (5) FOD and debond areas provided an opportunity for a leak path; and (6) there is still...
Topics: NASA Technical Reports Server (NTRS), FAILURE ANALYSIS, LEAKAGE, MICROCRACKS, X-33 REUSABLE LAUNCH...
The goal of the Reusable Launch Vehicle (RLV) technology program is formulated, and the primary objectives of RLV are listed. RLV technology program implementation phases are outlined. X-33 advanced technology demonstrator is described. Program management is addressed.
Topics: NASA Technical Reports Server (NTRS), TECHNOLOGIES, SINGLE STAGE TO ORBIT VEHICLES, X-33 REUSABLE...
In this paper, we present a direct fault tolerant control (DFTC) technique, where by "direct" we mean that no explicit fault identification is used. The technique will be presented for the attitude controller (autopilot) for a reusable launch vehicle (RLV), although in principle it can be applied to many other applications. Any partial or complete failure of control actuators and effectors will be inferred from saturation of one or more commanded control signals generated by the...
Topics: NASA Technical Reports Server (NTRS), ACTUATORS, ALTITUDE CONTROL, ATTITUDE CONTROL, CONTROL...
No abstract available
Topics: NASA Technical Reports Server (NTRS), COMPOSITE STRUCTURES, COMPOSITE MATERIALS, CRYOGENIC TANKS,...
This paper presents results of wind-tunnel tests that demonstrate a novel drag reduction technique for blunt-based vehicles. For these tests, the forebody roughness of a blunt-based model was modified using micomachined surface overlays. As forebody roughness increases, boundary layer at the model aft thickens and reduces the shearing effect of external flow on the separated flow behind the base region, resulting in reduced base drag. For vehicle configurations with large base drag, existing...
Topics: NASA Technical Reports Server (NTRS), WIND TUNNEL TESTS, AERODYNAMIC DRAG, BASE FLOW, DRAG...
A methodology is presented for the flutter analysis of the seal of thermal protection system (TPS) panel of X-33 Advanced Technology Demonstrator test vehicle. The seal is simulated as a two-dimensional cantilevered panel with an elastic stopper, which is modeled as an equivalent spring. This cantilever beam-spring model under the aerodynamic pressure at supersonic speeds turns out to be an impact nonlinear dynamic system. The flutter analysis of the seal is thus carried out using, time domain...
Topics: NASA Technical Reports Server (NTRS), ACOUSTIC FATIGUE, BOUNDARIES, DISPLACEMENT, FLUTTER ANALYSIS,...
Mission: Common upper stage engine for Ares I and Ares V. Challenge: Use proven technology from Saturn X-33, RS-68 to develop the highest Isp GG cycle engine in history for 2 missions in record time . Key Features: LOX/LH2 GG cycle, series turbines (2), HIP-bonded MCC, pneumatic ball-sector valves, on-board engine controller, tube-wall regen nozzle/large passively-cooled nozzle extension, TEG boost/cooling . Development Philosophy: proven hardware, aggressive schedule, early risk reduction,...
Topics: NASA Technical Reports Server (NTRS), ARES 5 CARGO LAUNCH VEHICLE, X-33 REUSABLE LAUNCH VEHICLE,...
The X-33 Guidance, Navigation, and Control (GN&C) Peer Review Team (PRT) was formed to assess the integrated X-33 vehicle GN&C system in order to identify any areas of disproportionate risk for initial flight. The eventual scope of the PRT assessment encompasses the GN&C algorithms, software, avionics, control effectors, applicable models, and testing. The initial (phase 1) focus of the PRT was on the GN&C algorithms and the Flight Control Actuation Subsystem (FCAS). The PRT...
Topics: NASA Technical Reports Server (NTRS), X-33 REUSABLE LAUNCH VEHICLE, GUIDANCE (MOTION), FLIGHT...
Wide band plume radiation data were collected during ten sea level tests of a single XRS-2200 engine at the NASA Stennis Space Center in 1999 and 2000. The XRS-2200 is a liquid hydrogen/liquid oxygen fueled, gas generator cycle linear aerospike engine which develops 204,420 lbf thrust at sea level. Instrumentation consisted of six hemispherical radiometers and one narrow view radiometer. Test conditions varied from 100% to 57% power level (PL) and 6.0 to 4.5 oxidizer to fuel (O/F) ratio....
Topics: NASA Technical Reports Server (NTRS), AEROSPIKE ENGINES, PLUMES, X-33 REUSABLE LAUNCH VEHICLE, HEAT...
Two methods for control system reconfiguration have been investigated. The first method is a robust servomechanism control approach (optimal tracking problem) that is a generalization of the classical proportional-plus-integral control to multiple input-multiple output systems. The second method is a control-allocation approach based on a quadratic programming formulation. A globally convergent fixed-point iteration algorithm has been developed to make onboard implementation of this method...
Topics: NASA Technical Reports Server (NTRS), CONTROL SYSTEMS DESIGN, MIMO (CONTROL SYSTEMS), X-33 REUSABLE...
Two methods for control system reconfiguration have been investigated. The first method is a robust servomechanism control approach (optimal tracking problem) that is a generalization of the classical proportional-plus-integral control to multiple input-multiple output systems. The second method is a control-allocation approach based on a quadratic programming formulation. A globally convergent fixed-point iteration algorithm has been developed to make onboard implementation of this method...
Topics: NASA Technical Reports Server (NTRS), FLIGHT CONTROL, SERVOMECHANISMS, PROPORTIONAL CONTROL, MIMO...
An online entry guidance algorithm has been developed using a predictor-corrector approach. The algorithm is designed for the Reusable Launch Vehicle (RLV) and is demonstrated by using, the X-33 model. The objective of the design is to handle widely dispersed entry conditions and deliver the vehicle at the Terminal Area Energy Management (TAEM) interface box within an acceptable tolerance and without violating any of the vehicle physical constraints. Combination of several control variables is...
Topics: NASA Technical Reports Server (NTRS), X-33 REUSABLE LAUNCH VEHICLE, PREDICTOR-CORRECTOR METHODS,...
Propellant densification has been identified as a critical technology in the development of single-stage-to-orbit reusable launch vehicles. Technology to create supercooled high-density liquid oxygen (LO2) and liquid hydrogen (LH2) is a key means to lowering launch vehicle costs. The densification of cryogenic propellants through subcooling allows 8 to 10 percent more propellant mass to be stored in a given unit volume, thereby improving the launch vehicle's overall performance. This allows for...
Topics: NASA Technical Reports Server (NTRS), LIQUID OXYGEN, GROUND TESTS, REUSABLE LAUNCH VEHICLES,...
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390
May 23, 2011
05/11
by
Balakrishnan, Narayani V.; Hou, Gen
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High-speed vehicles such as the Space Shuttle Orbiter must withstand severe aerodynamic heating during reentry through the atmosphere. The Shuttle skin and substructure are constructed primarily of aluminum, which must be protected during reentry with a thermal protection system (TPS) from being overheated beyond the allowable temperature limit, so that the structural integrity is maintained for subsequent flights. High-temperature reusable surface insulation (HRSI), a popular choice of passive...
Topics: OPTICAL MEASUREMENT, RAMAN SPECTROSCOPY, LASER INDUCED FLUORESCENCE, FLAMES, LIGHT SCATTERING,...
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173
Jun 9, 2011
06/11
by
Glaessgen, E. H.; Riddell, W. T.; Raju, I. S
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The effects of several critical assumptions and parameters on the computation of strain energy release rates for delamination and debond configurations modeled with plate elements have been quantified. The method of calculation is based on the virtual crack closure technique (VCCT), and models that model the upper and lower surface of the delamination or debond with two-dimensional (2D) plate elements rather than three-dimensional (3D) solid elements. The major advantages of the plate element...
Topics: AERODYNAMIC CHARACTERISTICS, AERODYNAMIC HEATING, COMPUTATIONAL FLUID DYNAMICS, FLIGHT CONDITIONS,...
This paper presents radiation data for the linear aerospike engine.
Topics: NASA Technical Reports Server (NTRS), AEROSPIKE ENGINES, PLUMES, X-33 REUSABLE LAUNCH VEHICLE, SEA...
An array of metallic Thermal Protection System (TPS) panels developed for the windward surface of the X-33 vehicle was tested in the 8-Foot High Temperature Tunnel at the NASA Langley Research Center. These tests were the first aerothermal tests of an X-33 TPS array and the test results will be used to validate the TPS for the X-33 flight program. Specifically, the tests evaluated the structural and thermal performance of the TPS, the effectiveness of the high temperature seals between adjacent...
Topics: NASA Technical Reports Server (NTRS), AEROTHERMODYNAMICS, THERMAL PROTECTION, SURFACE VEHICLES,...
Laminar and turbulent heating-rate calculations from an "engineering" code and laminar calculations from a "benchmark" Navier-Stokes code are compared with experimental wind-tunnel data obtained on several candidate configurations for the X-33 Phase 2 flight vehicle. The experimental data were obtained at a Mach number of 6 and a freestream Reynolds number ranging from 1 to 8 x 10(exp 6)/ft. Comparisons are presented along the windward symmetry plane and in a circumferential...
Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC HEATING, X-33 REUSABLE LAUNCH VEHICLE, WIND...
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283
May 27, 2011
05/11
by
Han, Samuel S
texts
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An RBCC engine combines air breathing and rocket engines into a single engine to increase the specific impulse over an entire flight trajectory. Considerable research pertaining to RBCC propulsion was performed during the 1960's and these engines were revisited recently as a candidate propulsion system for either a single-stage-to-orbit (SSTO) or two-stage-to-orbit (TSTO) launch vehicle. There are a variety of RBCC configurations that had been evaluated and new designs are currently under...
Topics: WIND TUNNEL TESTS, DESIGN ANALYSIS, X-33 REUSABLE LAUNCH VEHICLE, PREDICTION ANALYSIS TECHNIQUES,...
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The Sea-viewing Wide Field-of-view Sensor (SeaWiFS) is the follow-on ocean color instrument to the Coastal Zone Color Scanner (CZCS), which ceased operations in 1986, after an eight-year mission. SeaWiFS was launched on 1 August 1997, onboard the OrbView-2 satellite, built by Orbital Sciences Corporation (OSC). The SeaWiFS Project at the National Aeronautics and Space Administration (NASA) Goddard Space Flight Center (GSFC), undertook the responsibility of documenting all aspects of this...
Topics: ENGINE TESTS, FULL SCALE TESTS, PROPELLANT TESTS, TEST FACILITIES, X-33 REUSABLE LAUNCH VEHICLE,...
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May 31, 2011
05/11
by
Patnaik, Surya N.; Hopkins, Dale A
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The theory of elasticity evolved over centuries through the contributions of eminent scientists like Cauchy, Navier, Hooke Saint Venant, and others. It was deemed complete when Saint Venant provided the strain formulation in 1860. However, unlike Cauchy, who addressed equilibrium in the field and on the boundary, the strain formulation was confined only to the field. Saint Venant overlooked the compatibility on the boundary. Because of this deficiency, a direct stress formulation could not be...
Topics: X-33 REUSABLE LAUNCH VEHICLE, ACTUATORS, STABILITY, CONFIGURATION MANAGEMENT, CONTROL SYSTEMS...
Advanced, waveform based acoustic emission (AE) techniques have been previously used to evaluate damage progression in laboratory tests of composite coupons. In these tests, broad band, high fidelity acoustic sensors were used to detect signals which were then digitized and stored for analysis. Analysis techniques were based on plate mode wave propagation characteristics. This approach, more recently referred to as Modal AE, provides an enhanced capability to discriminate and eliminate noise...
Topics: NASA Technical Reports Server (NTRS), ACOUSTIC EMISSION, COMPOSITE MATERIALS, WAVEFORMS, ACOUSTIC...
A series of uni-element rocket injector studies were completed to provide benchmark quality data needed to validate computational fluid dynamic models. A shear coaxial injector geometry was selected as the primary injector for study using gaseous hydrogen/oxygen and gaseous hydrogen/liquid oxygen propellants. Emphasis was placed on the use of non-intrusive diagnostic techniques to characterize the flowfields inside an optically-accessible rocket chamber. Measurements of the velocity and species...
Topics: NASA Technical Reports Server (NTRS), COMPUTATIONAL FLUID DYNAMICS, GAS-GAS INTERACTIONS, DYNAMIC...
The X-33 reusable launch vehicle demonstrator has identified the need to implement a vehicle health monitoring system that can acquire data that monitors system health and performance. Sanders, a Lockheed Martin Company, has designed and developed a COTS-based open architecture system that implements a number of technologies that have not been previously used in a flight environment. NASA Dryden Flight Research Center and Sanders teamed to demonstrate that the distributed remote health nodes,...
Topics: NASA Technical Reports Server (NTRS), X-33 REUSABLE LAUNCH VEHICLE, SYSTEMS HEALTH MONITORING,...
The slide presentation examines the role of customer and stakeholder relations in the success of space missions. Topics include agency transformation; an overview of project and program experience with a discussion of positions, technical accomplishments, and management lessons learned; and approaches to project success with emphasis on communication. Projects and programs discussed include the Space Shuttle Main Engine System, DC-XA Flight Demonstrator, X-33 Flight Demonstrator, Space Launch...
Topics: NASA Technical Reports Server (NTRS), SPACE MISSIONS, PROJECT MANAGEMENT, COMMUNICATION, NASA...
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226
May 29, 2011
05/11
by
Choi, Michael K
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Landsat-7 was successfully launched into orbit on April 15, 1999. After devoting three months to the t bakeout and cool-down of the radiative cooler, and on- t orbit checkout, the Enhanced Thematic Mapper Plus (ETM) began the normal imaging phase of the mission in mid-July 1999. This paper presents the thermal performance of the ETM from mid-July 1999 to mid-May 2000. The flight temperatures are compared to the yellow temperature limits, and worst cold case and worst hot case flight temperature...
Topics: SPACECRAFT GUIDANCE, FLIGHT SAFETY, RISK, CONTROL SYSTEMS DESIGN, SPACECRAFT CONTROL, X-33 REUSABLE...
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May 29, 2011
05/11
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Mikic, Zora
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This report covers technical progress during the third year of the NASA Space Physics Theory contract ''The Structure and Dynamics of the Solar Corona,'' between NASA and Science Applications International Corporation, and covers the period June 16, 1998 to August 15, 1999. This is also the final report for this contract. Under this contract SAIC, the University of California, Irvine (UCI), and the Jet Propulsion Laboratory (JPL), have conducted research into theoretical modeling of active...
Topics: REUSABLE LAUNCH VEHICLES, STORAGE TANKS, PROPELLANT TANKS, EXTERNAL TANKS, LIQUID OXYGEN,...
All space vehicles require ground umbilical systems for servicing. Servicing requirements can include, but are not limited to, electrical power and control, propellant loading and venting, pneumatic system supply, hazard gas detection and purging as well as systems checkout capabilities. Of the various types of umbilicals, all require several common subsystems. These typically include an alignment system, mating and locking system, fluid connectors, electrical connectors and control !checkout...
Topics: NASA Technical Reports Server (NTRS), LAUNCHING, ELECTRIC CONNECTORS, GROUND SUPPORT SYSTEMS, GAS...
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May 26, 2011
05/11
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DeLand, Matthew T.; Cebula, Richard P.; Hilsenrath, Ernes
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The Shuttle SBUV (SSBUV) and NOAA-11 SBUV/2 instruments measured solar spectral UV irradiance during the maximum and declining phase of solar cycle 22. The SSB UV data accurately represent the absolute solar UV irradiance between 200-405 nm, and also show the long-term variations during eight flights between October 1989 and January 1996. These data have been used to correct long-term sensitivity changes in the NOAA-11 SBUV/2 data, which provide a near-daily record of solar UV variations over...
Topics: X-33 REUSABLE LAUNCH VEHICLE, MAINTENANCE, DECISION MAKING, SMART STRUCTURES, COST REDUCTION,...
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May 27, 2011
05/11
by
Scialdone, John J
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At various time concerns have been expressed that rapid decompressions of compartments of gas pockets and thermal blankets during spacecraft launches may have caused pressure differentials across their walls sufficient to cause minor structural failures, separations of adhesively-joined parts, ballooning, and flapping of blankets. This paper presents a close form equation expressing the expected pressure differentials across the walls of a compartment as a function of the external to the volume...
Topics: X-33 REUSABLE LAUNCH VEHICLE, TRANSITION FLIGHT, CONTROL ROCKETS, GUIDANCE SENSORS,...
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May 29, 2011
05/11
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NON
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This supplemental issue of Aerospace Medicine and Biology, A Continuing Bibliography with Indexes (NASA/SP#1999-7011) lists reports, articles, and other documents recently announced in the NASA STI Database. In its subject coverage, Aerospace Medicine and Biology concentrates on the biological, physiological, psychological, and environmental effects to which humans are subjected during and following simulated or actual flight in the Earth#s atmosphere or in interplanetary space. References...
Topics: SPACECRAFT DESIGN, SPACE SHUTTLE BOOSTERS, NUCLEAR PROPULSION, SPACE SHUTTLES, SPACE TRANSPORTATION...
