Wernher von Braun

National Aeronautics and Space Administration (NASA)

World Spaceflight News

With the success of the Apollo 11 landing on the Moon, Wernher von Braun presented an ambitious plan for manned missions to Mars as soon as the 1980s to the Space Task Group for consideration by President Richard Nixon as the next step in America's space program. Nixon rejected the plan, and the goal of humans on Mars remains unfulfilled. Here are the technical details of his incredible nuclear rocket powered proposal, which was based on studies by Boeing in 1968. Contents: Boeing 1968 Study Volume 1 * Boeing 1968 Study Volume 2 * 1969 von Braun Manned Mars Mission Proposal * von Braun's Integrated Space Program, 1970-1990. In his presentation, von Braun wrote: With the recent accomplishment of the manned lunar landing, the next frontier is manned exploration of the planets. Perhaps the most significant scientific question is the possibility of extraterrestrial life in our solar system. Manned planetary flight provides the opportunity to resolve this universal question thus capturing international interest and cooperation. The information presented here describes a method of landing men on the planet Mars in 1982. The scientific goals of the mission are described and the key decision dates are identified. The 1981 manned Mars mission (1982 landing on Mars) is shown as an integral part of the total space program for the next two decades. The systems and experience resulting from the Apollo program and the missions proposed for the 1970's provide the technical and programmatic foundation for this undertaking. A 1982 manned Mars landing is a logical focus for the programs of the next decade. Although the undertaking of this mission will be a great national challenge, it represents no greater challenge than the commitment made in 1961 to land a man on the moon. Several different modes are possible for accomplishing Mars landing missions, each with its peculiar advantages and disadvantages. The typical Mars Landing Mission begins with the boost of the planetary vehicle elements into Earth orbit utilizing the Saturn V and Space Shuttle vehicles. Following assembly of the complete planetary vehicle in Earth orbit, the Earth departure phase of the mission is initiated. The Mars vehicle then begins a 270-day journey to Mars. This is by no means an idle phase of the mission. In addition to observations of Mars, many other experiments and measurements will be made on both the Earth-to-Mars and Mars-to-Earth legs of the trip that are of prime scientific importance. The spacecraft represents a manned laboratory in space, free of the disturbing influences of the Earth. The fact that there will be two observation points, Earth and the spacecraft, permits several possible experiments regarding the temporal and spatial features of the interplanetary environment. In addition, the spacecraft can be used to supplement and extend numerous observations conducted from Earth orbital space stations, particularly in the field of astronomy. It is possible, for example, that as yet unidentified comets might be observed for the first time.

Wernher Von Braun's 1969 Manned Mars Mission Plans After Apollo and the Boeing 1968 Integrated Manned Interplanetary Nuclear Spacecraft Concept Definition Study

This article considers a quaternary direct-sequence code-division multiple-access (DS-CDMA) communication system with asymmetric quadrature phase-shift-keying (AQPSK) modulation for unequal error protection (UEP) capability. Both time synchronous and asynchronous cases are investigated. An expression for the probability distribution of the multiple-access interference is derived. The exact bit-error performance and the approximate performance using a Gaussian approximation and random signature sequences are evaluated by extending the techniques used for uniform quadrature phase-shift-keying (QPSK) and binary phase-shift-keying (BPSK) DS-CDMA systems. Finally, a general system model with unequal user power and the near-far problem is considered and analyzed. The results show that, for a system with UEP capability, the less protected data bits are more sensitive to the near-far effect that occurs in a multiple-access environment than are the more protected bits.Wang, C.-W. and Stark, W.Jet Propulsion LaboratoryQUADRATURE PHASE SHIFT KEYING; BINARY PHASE SHIFT KEYING; ASYMMETRY; CODE DIVISION MULTIPLE ACCESS; PHASE SHIFT KEYING; MULTIPLE ACCESS; PROTECTION; RELIABILITY ANALYSIS

Performance Analysis of Direct-Sequence Code-Division Multiple-Access Communications with Asymmetric Quadrature Phase-Shift-Keying Modulation

An investigation was conducted in the Langley Unitary Plan Wind Tunnel at Mach numbers from 1.6 to 4.5. The model had a low-aspect-ratio body with a flat undersurface. A center fin and two outboard fins were mounted on the aft portion of the upper body. The outboard fins were rolled outboard 40 deg from the vertical. Elevon surfaces made up the trailing edges of the outboard fins, and body flaps were located on the upper and lower aft fuselage. The center fin pivoted about its midchord for yaw control. The model was longitudinally stable about the design center-of-gravity position at 54 percent of the body length. The configuration with undeflected longitudinal controls trimmed near 0 deg angle of attack at Mach numbers from 1.6 to 3.0 where lift and lift-drag ratio were negative. Longitudinal trim was near the maximum lift-drag ratio (1.4) at Mach 4.5. The model was directionally stable over Mach number range except at angles of attack around 4 deg at M = 2.5. Pitch control deflection of more than -10 deg with either elevons or body flaps is needed to trim the model to angles of attack at which lift becomes positive. With increased control deflection, the lifting-body configuration should perform the assured crew return mission through the supersonic speed range. Ware, George M. Langley Research Center...

Supersonic Aerodynamic Characteristics of a Proposed Assured Crew Return Capability (Acrc) Lifting-Body Configuration

During 2003 and 2004, the Johnson Space Center's White Sands Testing Facility in Las Cruces, New Mexico conducted hypervelocity impact tests on the space shuttle wing leading edge. Hypervelocity impact tests were conducted to determine if Micro-Meteoroid/Orbital Debris impacts could be reliably detected and located using simple passive ultrasonic methods. The objective of Targets A-1, A-2, and B-2 was to study hypervelocity impacts through multi-layered panels simulating Whipple shields on spacecraft. Impact damage was detected using lightweight, low power instrumentation capable of being used in flight. Gorman, Michael R. and Ziola, Steven M. Langley Research Center HYPERVELOCITY IMPACT; GLASS FIBERS; PANELS; LEADING EDGES; SIMULATION; WINGS; TARGETS; IMPACT TESTS; SPACE DEBRIS; DETECTION; SIGNAL TRANSMISSION; METEORITE COLLISIONS; WAVEFORMS; KINETIC ENERGY; LINEARITY; ELECTROMAGNETIC INTERFERENCE; TEST FACILITIES

Hypervelocity Impact (Hvi). Volume 2; Wle Small-Scale Fiberglass Panel Flat Multi-Layer Targets A-1, A-2, and B-1

During 2003 and 2004, the Johnson Space Center's White Sands Testing Facility in Las Cruces, New Mexico conducted hypervelocity impact tests on the space shuttle wing leading edge. Hypervelocity impact tests were conducted to determine if Micro-Meteoroid/Orbital Debris impacts could be reliably detected and located using simple passive ultrasonic methods. The objective of Target C-1 was to study hypervelocity impacts on the reinforced carbon-carbon (RCC) panels of the Wing Leading Edge. Fiberglass was used in place of RCC in the initial tests. Impact damage was detected using lightweight, low power instrumentation capable of being used in flight. Gorman, Michael R. and Ziola, Steven M. Langley Research Center HYPERVELOCITY IMPACT; WINGS; LEADING EDGES; PANELS; GLASS FIBERS; TARGETS; CARBON-CARBON COMPOSITES; MICROMETEOROIDS; DEBRIS; IMPACT DAMAGE; DETECTION; ELECTROMAGNETIC INTERFERENCE; KINETIC ENERGY; WAVE PROPAGATION

Hypervelocity Impact (Hvi). Volume 3; Wle Small-Scale Fiberglass Panel Flat Target C-1

During 2003 and 2004, the Johnson Space Center's White Sands Testing Facility in Las Cruces, New Mexico conducted hypervelocity impact tests on the space shuttle wing leading edge. Hypervelocity impact tests were conducted to determine if Micro-Meteoroid/Orbital Debris impacts could be reliably detected and located using simple passive ultrasonic methods. The objective of Target C-2 was to study impacts through the reinforced carboncarbon (RCC) panels of the Wing Leading Edge. Fiberglass was used in place of RCC in the initial tests. Impact damage was detected using lightweight, low power instrumentation capable of being used in flight. Gorman, Michael R. and Ziola, Steven M. Langley Research Center GLASS FIBERS; HYPERVELOCITY IMPACT; LEADING EDGES; PANELS; TARGETS; WINGS; SPACE SHUTTLES; CARBON-CARBON COMPOSITES; TEST FACILITIES; ACOUSTIC EMISSION; SIGNAL TRANSMISSION; ELECTROMAGNETIC WAVE TRANSMISSION; WAVE PROPAGATION; KINETIC ENERGY; IMPACT TESTS; WAVEFORMS; IMPACT VELOCITY

Hypervelocity Impact (Hvi). Volume 4; Wle Small-Scale Fiberglass Panel Flat Target C-2

There is a need to explore methods for reducing lengthly computer turnaround or clock time associated with engineering design problems. Different strategies can be employed to reduce this turnaround time. One strategy is to run validated analysis software on a network of existing smaller computers so that portions of the computation can be done in parallel. This paper focuses on the implementation of this method using two types of problems. The first type is a traditional structural design optimization problem, which is characterized by a simple data flow and a complicated analysis. The second type of problem uses an existing computer program designed to study multilevel optimization techniques. This problem is characterized by complicated data flow and a simple analysis. The paper shows that distributed computing can be a viable means for reducing computational turnaround time for engineering design problems that lend themselves to decomposition. Parallel computing can be accomplished with a minimal cost in terms of hardware and software. Young, Katherine C. and Padula, Sharon L. and Rogers, James L. Langley Research Center NASA-TM-101519, NAS 1.15:101519 RTOP 505-63-01-07...

A Strategy for Reducing Turnaround Time in Design Optimization Using a Distributed Computer System

The noise of advanced high speed propeller models measured in the NASA 8- by 6-foot wind tunnel has been compared with model propeller noise measured in another tunnel and with full-scale propeller noise measured in flight. Good agreement was obtained for the noise of a model counterrotation propeller tested in the 8- by 6-foot wind tunnel and in the acoustically treated test section of the Boeing Transonic Wind Tunnel. This good agreement indicates the relative validity of taking cruise noise data on a plate in the 8- by 6-foot wind tunnel compared with the free-field method in the Boeing tunnel. Good agreement was also obtained for both single rotation and counter-rotation model noise comparisons with full-scale propeller noise in flight. The good scale model to full-scale comparisons indicate both the validity of the 8- by 6-foot wind tunnel data and the ability to scale to full size. Boundary layer refraction on the plate provides a limitation to the measurement of forward arc noise in the 8- by 6-foot wind tunnel at the higher harmonics of the blade passing tone. The use of a validated boundary layer refraction model to adjust the data could remove this limitation. Dittmar, James H. Glenn Research Center NASA-TM-101976, E-4676, NAS 1.15:101976, AIAA PAPER 89-1059 RTOP 535-03-01...

Comparison of Propeller Cruise Noise Data Taken in the NASA Lewis 8- By 6-Foot Wind Tunnel with Other Tunnel and Flight Data

This is the final report and addresses all of the work performed on this program. Specifically, it covers vehicle architecture background, definition of six baseline engine cycles, reliability baseline (space shuttle main engine QRAS), and component level reliability/performance/cost for the six baseline cycles, and selection of 3 cycles for further study. This report further addresses technology improvement selection and component level reliability/performance/cost for the three cycles selected for further study, as well as risk reduction plans, and recommendation for future studies. Matlock, Steve Marshall Space Flight Center NAS8-00168

Pratt & Whitney Propulsion Risk Reduction Requirements Program (Ta-3 & Ta-4)

2nd Generation Rlv Risk Reduction Definition Program

Solar Electric Propulsion (SEP) when used for station keeping and final orbit insertion has been shown to increase a geostationary satellite's payload when launched by existing expendable launch vehicles. In the case of reusable launch vehicles or expendable launch vehicles where an upper stage is an expensive option, this methodology can be modified by using the existing on-board apogee chemical system to perform a perigee burn and then letting the electric propulsion system complete the transfer to geostationary orbit. The elimination of upper stages using on-board chemical and electric propulsion systems was thus examined for GEO spacecraft. Launch vehicle step-down from an Atlas IIAR to a Delta 7920 (no upper stage) was achieved using expanded on-board chemical tanks, 40 kW payload power for electric propulsion, and a 60 day elliptical to GEO SEP orbit insertion. Optimal combined chemical and electric trajectories were found using SEPSPOT. While Hall and ion thrusters provided launch vehicle step-down and even more payload for longer insertion times, NH3 arcjets had insufficient performance to allow launch vehicle step-down. Degradation levels were only 5% to 7% for launch step-down cases using advanced solar arrays. Results were parameterized to allow comparisons for future reusable launch vehicles. Results showed that for an 8 W/kg initial power/launch mass power density spacecraft, 50% to 100% more payload can be launched using this method. Oleson, Steven Glenn Research Center NASA/TM-1999-209646, NAS 1.15:209646, IEPC-99-185, E-11994

Advanced Electric Propulsion for Rlv Launched Geosynchronous Spacecraft

This is a revised final report and addresses all of the work performed on this program. Specifically, it covers vehicle architecture background, definition of six baseline engine cycles, reliability baseline (space shuttle main engine QRAS), and component level reliability/performance/cost for the six baseline cycles, and selection of 3 cycles for further study. This report further addresses technology improvement selection and component level reliability/performance/cost for the three cycles selected for further study, as well as risk reduction plans, and recommendation for future studies. Matlock, Steve and Sides, Steve and Kmiec, Tom and Arbogast, Tim and Mayers, Tom and Doehnert, Bill Marshall Space Flight Center NAS8-00168; NRA8-27

2nd Generation Reusable Launch Vehicle (2g Rlv). Revised

In this final report regarding support to the second generation RLV (Reusable Launch Vehicle) propulsion project office, a list of tasks accomplished is presented. During this period, Lee & Associates, LLC participated in numerous Systems Requirements Reviews (SRR) related to the Cobra development program. Lee, Thomas J. Marshall Space Flight Center

Support to 2nd Generation Rlv Propulsion Project Office

The National Aeronautics and Space Administration is considering a vertical lander as a candidate concept for a single-stage-to-orbit reusable launch vehicle (RLV). Three strategies for guiding and controlling the inversion of a reentering RLV from a nose-first attitude to a vertical landing attitude are suggested. Each option is simulated from a common reentry state to touchdown, using a common guidance algorithm and different controllers. Results demonstrate the characteristics that typify and distinguish each concept and help to identify peculiar problems, level of guidance and control sophistication required, feasibility concerns, and areas in which stringent subsystem requirements will be imposed by guidance and control. Gallaher, M. and Coughlin, D. and Krupp, D Marshall Space Flight Center...

A Guidance and Control Assessment of Three Vertical Landing Options for Rlv

Jade is a new distribution file system that provides a uniform way to name and access files in an internet environment. It makes two important contributions. First, Jade is a logical system that integrates a heterogeneous collection of existing file systems, where heterogeneous means that the underlying file systems support different file access protocols. Jade is designed under the restriction that the underlying file system may not be modified. Second, rather than providing a global name space, Jade permits each user to define a private name space. These private name spaces support two novel features: they allow multiple file systems to be mounted under one directory, and they allow one logical name space to mount other logical name spaces. A prototype of the Jade File System was implemented on Sun Workstations running Unix. It consists of interfaces to the Unix file system, the Sun Network File System, the Andrew File System, and FTP. This paper motivates Jade's design, highlights several aspects of its implementation, and illustrates applications that can take advantage of its features. Peterson, Larry L. and Rao, Herman C. Unspecified Center NSF CCR-88-11423; NSF NCR-90-05028; NCC2-561...

The Jade File System

Accessing Files in an Internet

Our project included a variety of activities, ranging from model development to data manipulation and even participation in the SHEBA and FIRE field experiments. The following sections outline the work accomplished under these tasks. A collection of reprints is attached to this report. Randell, David A. Langley Research Center

Interactions of the Cloudy Arctic Boundary Layer with Variable Surface Conditions and Large-Scale Circulations

For 5 years, the cooperative agreement NCC3-763 has focused on the development and understanding of Sic-based composites. Most of the work was performed in the area of SiC fiber-reinforced composites for UEET and NGLT and in collaboration with Goodrich Corporation under a partially reimbursable Space Act Agreement. A smaller amount of work was performed on C fiber-reinforced SiC matrix composites for NGLT. Major accomplishments during this agreement included: Improvements to the interphase used in melt-infiltrated (MI) SiC/SiC composites which increases the life under stressed-oxidation at intermediate temperatures referred to as "outside-debonding". This concept is currently in the patent process and received a Space Act Award. Mechanistic-based models of intermediate temperature degradation for MI SiC/SiC Quantification and relatively robust relationships for matrix crack evolution under stress in SiC/SiC composites which serve as the basis for stress-strain and elevated temperature life models The furthering of acoustic emission as a useful tool in composite damage evolution and the extension of the technique to other composite systems Development of hybrid C-SiC fiber-reinforced SiC matrix composites Numerous presentations at conferences, industry partners, and government centers and publications in recognized proceedings and journals. Other recognition of the author's accomplishments by NASA with a TGIR award (2004), NASA's Medal for Public Service (2004), and The American Ceramic Society s Richard M. Fulrath Award (2005). The following will briefly describe the work of the past five years in the three areas of interest: SiC/SiC composite development, mechanistic understanding and modeling of SiC/SiC composites, and environmental durability of C/SiC composites. More detail can be found in the publications cited at the end of this report. Glenn Research Center

Factors Controlling Elevated Temperature Strength Degradation of Silicon Carbide Composites

This guide describes the input data required, for steady or unsteady aerodynamic and aeroelastic analysis of propellers and the output files generated, in using PROP3D. The aerodynamic forces are obtained by solving three dimensional unsteady, compressible Euler equations. A normal mode structural analysis is used to obtain the aeroelastic equations, which are solved using either time domain or frequency domain solution method. Sample input and output files are included in this guide for steady aerodynamic analysis of single and counter-rotation propellers, and aeroelastic analysis of single-rotation propeller. Srivastava, R. and Reddy, T. S. R. Glenn Research Center...

A Program for 3D Euler Unsteady Aerodynamic and Aeroelastic (Flutter and Forced Response) Analysis of Propellers. Version 1.0

Prop3d

In this report the methodology adopted to measure unsteady pressures on blade surfaces in the NASA Transonic Flutter Cascade under conditions of simulated blade flutter is described. The previous work done in this cascade reported that the oscillating cascade produced waves, which for some interblade phase angles reflected off the wind tunnel walls back into the cascade, interfered with the cascade unsteady aerodynamics, and contaminated the acquired data. To alleviate the problems with data contamination due to the back wall interference, a method of influence coefficients was selected for the future unsteady work in this cascade. In this approach only one blade in the cascade is oscillated at a time. The majority of the report is concerned with the experimental technique used and the experimental data generated in the facility. The report presents a list of all test conditions for the small amplitude of blade oscillations, and shows examples of some of the results achieved. The report does not discuss data analysis procedures like ensemble averaging, frequency analysis, and unsteady blade loading diagrams reconstructed using the influence coefficient method. Finally, the report presents the lessons learned from this phase of the experimental effort, and suggests the improvements and directions of the experimental work for tests to be carried out for large oscillation amplitudes.Lepicovsky, J. and McFarland, E. R. and Capece, V. R. and Jett, T. A. and Senyitko, R. G.Glenn Research CenterTRANSONIC FLUTTER; UNSTEADY AERODYNAMICS; ROTARY WINGS; COMPUTERIZED SIMULATION; WIND TUNNELS; PRESSURE MEASUREMENT; DATA INTEGRATION; DATA PROCESSING; NUMERICAL ANALYSIS; PHASE SHIFT; INFLUENCE COEFFICIENT; WIND TUNNEL WALLS

Methodology of Blade Unsteady Pressure Measurement in the NASA Transonic Flutter Cascade

Morphology (the study of structure and form) of the octahedral-tetrahedral (octet) truss is described. Both the geometry and symmetry of the octet truss are considered. Morphological techniques based on symmetry operations are presented which enable the derivation of reduced-part-count truss configurations from the octet truss by removing struts and nodes. These techniques are unique because their Morphological origination and they allow for the systematic generation and analysis of a large variety of structures. Methods for easily determining the part count and redundancy of infinite truss configurations are presented. Nine examples of truss configurations obtained by applying the derivation techniques are considered. These configurations are structurally stable while at the same time exhibiting significant reductions in part count. Some practical and analytical considerations, such as structural performance, regarding the example reduced-part-count truss geometries are briefly discussed. Lalvani, Haresh and Collins, Timothy J. Langley Research Center MORPHOLOGY; STRUCTURAL ANALYSIS; STRUCTURAL STABILITY; SYMMETRY; TRUSSES; DESIGN ANALYSIS; OCTETS; REDUNDANCY; STRUTS...

Comparative Morphology of Configurations with Reduced Part Count Derived from the Octahedral-Tetrahedral Truss

We have delivered only 2 or 3 UV Holographic Optical Elements (HOEs) thus far and have fallen short of the intended goal in size and in dual wavelength function. Looking back, it has been fortuitous that we even made anything work in the UV region. It was our good fortune to discover that the material we work with daily was adequate for use at 355 nm, if well rinsed during processing. If we had stuck to our original plan of etching in small pieces of fused silica, we would still be trying to make the first small section in our ion mill, which is not yet operational. The original plan was far too ambitious and would take another 2 years to complete beginning where we left off this time. In order to make a HOE for the IR as well as the UV we will likely have to learn to sensitize some film to the 1064 line and we have obtained sensitizer that is reported to work in that region already. That work would also take an additional year to complete. Rallison, Richard D. and Schwemmer, Geary K. (Technical Monitor) Goddard Space Flight Center Rept-24

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