Alleviation of divergence during rocket launch Patent
Design and characteristics of linkage to alleviate rocket vehicle divergence during launch
Gillespie, W., Jr.↗
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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Propulsion/electrical power generation Final report
Generation of electric power with use of nuclear engine for rocket vehicles /NERVA/ heat source
Source record↗
Study of fluidic roll control for sounding rocket applications
Fluidic roll control for Aerobee rocket vehicle
Keltz, W. L.↗
Rocket measurement of the secondary electron spectrum in an aurora
Secondary electron emission measurement in aurora using Aerobee rocket vehicle
Doering, J. P.↗
Rocket measurements of upper atmospheric nitric oxide and their consequences to the lower ionosphere
Rocket measurements of nitric oxide density profile in upper atmosphere with scanning ultraviolet spectrometers aboard Nike-Apache rocket vehicle
Meira, L. G., Jr.↗
Single action separation mechanism Patent
Separation mechanism for use between stages of multistage rocket vehicles
Mccormack, W.↗
The Nike canted-fin Apache
Nike-Apache sounding rocket vehicle with canted fins, examining pitch-roll coupling characteristics by equilibrium and dynamic simulation methods
Mayo, E. E.↗
Laser propulsion
The use of an earth-based high-power laser beam to provide energy for earth-launched rocket vehicle is investigated. The laser beam energy is absorbed in an opaque propellant gas and is converted to high-specific-impulse thrust by expanding the heated propellant to space by means of a nozzle. This laser propulsion scheme can produce specific impulses of several thousand seconds. Payload to gross-weight fractions about an order of magnitude higher than those for conventional chemical earth-launched vehicles appear possible. There is a potential for a significant reduction in cost per payload mass in earth orbit.
Rom, F. E.↗
Shuttle/Agena study. Volume 2, part 2: Agena tug configurations, Shuttle/Agena interface, performance, safety, cost
An evaluation of the compatibility of the space shuttle and Agena rocket vehicle was conducted. The Agena space tug configuration design is described in terms of the total vehicle system as well as the individual subsystems and major assemblies and components. The complete interface between the Agena space tug and the space shuttle orbiter is defined for in-flight and ground operations. The derivation and design of an evolutionary stage is also presented. This vehicle conforms to the same guidelines and interface requirements as the Agena space tug. Performance data developed for both vehicles for each of the three study baseline missions are included.
Source record↗
Shuttle/Agena study. Annex A: Ascent agena configuration
Details are presented on the Agena rocket vehicle description, vehicle interfaces, environmental constraints and test requirements, software programs, and ground support equipment. The basic design concept for the Ascent Agena is identified as optimization of reliability, flexibility, performance capabilities, and economy through the use of tested and flight-proven hardware. The development history of the Agenas A, B, and D is outlined and space applications are described.
Source record↗
Self-acting and hydrodynamic shaft seals
Self-acting and hydrodynamic seals are described. The analytical procedures are outlined for obtaining a seal force balance and the operating film thickness. Particular attention is given to primary ring response (seal vibration) to rotating seat face runout. This response analysis revealed three different vibration modes. Proposed applications of self-acting seals in gas turbine engines and in rocket vehicle turbopumps are described. Also experimental data on self-acting face seals operating under simulated gas turbine conditions are given; these data show the feasibility of operating the seal at conditions of 345 newtons per square centimeter (500 psi) and 152 meters per second (500 ft/sec) sliding speed.
Ludwig, L. P.↗
Bypass control valve seal and bearing life cycle test report
The operating characteristics of a bypass control valve seal and bearing life cycle tests are reported. Data from the initial assembly, leak, torque, and deflection tests are included along with the cycle life test results and conclusions. The equipment involved was to be used in the nuclear engine for the rocket vehicles program.
Lundback, A. V.↗
LH2 pump component development testing in the electric pump room at test cell C inducer no. 1
The characteristics of a turbine pump for use with the nuclear engine for rocket vehicles are discussed. It was determined that the pump will be a two stage centrifugal pump with both stages having backswept impellers and an inducer upstream of the first stage impeller. The test program provided demonstration of the ability of the selected design to meet the imposed requirements.
Andrews, F. X.↗
Design and development of LH2 cooled rolling element radial bearings for the NERVA engine turbopump. Volume 3: Phase 2: Tests on build-ups 16, 17, and 18 at NRDS, Jackass Flats, Nevada, December 1971 - March 1972
The use of liquid hydrogen to cool the rolling element radial bearings in the nuclear engine for rocket vehicles is discussed. The fifteen hour service life goal was obtained during the tests. The increase in bearing life was also considered to be produced by: (1) improvements in bearing material, (2) bearing retainer configuration and manufacturing changes, and (3) better control of operating parameters.
Accinelli, J. B.↗
NERVA dynamic analysis methodology, SPRVIB
The general dynamic computer code called SPRVIB (Spring Vib) developed in support of the NERVA (nuclear engine for rocket vehicle application) program is described. Using normal mode techniques, the program computes kinematical responses of a structure caused by various combinations of harmonic and elliptic forcing functions or base excitations. Provision is made for a graphical type of force or base excitation input to the structure. A description of the required input format and a listing of the program are presented, along with several examples illustrating the use of the program. SPRVIB is written in FORTRAN 4 computer language for use on the CDC 6600 or the IBM 360/75 computers.
Vronay, D. F.↗
NASA/MSFC multilayer diffusion models and computer program for operational prediction of toxic fuel hazards
The NASA/MSFC multilayer diffusion models are discribed which are used in applying meteorological information to the estimation of toxic fuel hazards resulting from the launch of rocket vehicle and from accidental cold spills and leaks of toxic fuels. Background information, definitions of terms, description of the multilayer concept are presented along with formulas for determining the buoyant rise of hot exhaust clouds or plumes from conflagrations, and descriptions of the multilayer diffusion models. A brief description of the computer program is given, and sample problems and their solutions are included. Derivations of the cloud rise formulas, users instructions, and computer program output lists are also included.
Dumbauld, R. K.↗
Prediction of fluctuating pressure environments associated with plume-induced separated flow fields
The separated flow environment induced by underexpanded rocket plumes during boost phase of rocket vehicles has been investigated. A simple semi-empirical model for predicting the extent of separation was developed. This model offers considerable computational economy as compared to other schemes reported in the literature, and has been shown to be in good agreement with limited flight data. The unsteady pressure field in plume-induced separated regions was investigated. It was found that fluctuations differed from those for a rigid flare only at low frequencies. The major difference between plume-induced separation and flare-induced separation was shown to be an increase in shock oscillation distance for the plume case. The prediction schemes were applied to PRR shuttle launch configuration. It was found that fluctuating pressures from plume-induced separation are not as severe as for other fluctuating environments at the critical flight condition of maximum dynamic pressure.
Plotkin, K. J.↗
Development of the Astrobee F sounding rocket system.
The development of the Astrobee F sounding rocket vehicle through the first flight test at NASA-Wallops Station is described. Design and development of a 15 in. diameter, dual thrust, solid propellant motor demonstrating several new technology features provided the basis for the flight vehicle. The 'F' motor test program described demonstrated the following advanced propulsion technology: tandem dual grain configuration, low burning rate HTPB case-bonded propellant, and molded plastic nozzle. The resultant motor integrated into a flight vehicle was successfully flown with extensive diagnostic instrumentation.-
Jenkins, R. B.↗