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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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At least 1,171 records · Page 65
All sourcesNASA NTRSDOE OSTI
NASA NTRS2019

Reconstruction of the Advanced Supersonic Parachute Inflation Research Experiment Sounding Rocket Flight Tests with Strengthened Disk-Gap-Band Parachute

The Advanced Supersonic Parachute Inflation Research and Experiments project is a flight test program for development of supersonic parachutes for future use at Mars. The flight tests are a risk-reduction program for the Mars 2020 mission. The flight tests involve two Disk-Gap- Band parachute designs to be tested at relevant Mach number and dynamic pressure regimes for the Mars 2020 entry capsule. The first of these parachutes is a built-to-print design that was successfully employed by the Mars Science Laboratory lander at Mars in August 2012, and the second is a design that is strengthened in material properties and construction methods but has the same geometry as that used by Mars Science Laboratory. The first flight test of the built-to-print parachute took place on October 4, 2017 at NASA's Wallops Flight Facility. The parachute test was successful. The second and third flight tests took place on March 31st and September 7th 2018, respectively, and successfully tested the strengthened parachute design. This paper describes the instrumentation, data analysis techniques, and atmospheric and trajectory reconstruction results from the second and third flight tests.

Karlgaard, Christopher D.↗
NASA NTRS2002

An Engine Research Program Focused on Low Pressure Turbine Aerodynamic Performance

A comprehensive test program was performed in the Propulsion Systems Laboratory at the NASA Glenn Research Center, Cleveland Ohio using a highly instrumented Pratt and Whitney Canada PW 545 turbofan engine. A key objective of this program was the development of a high-altitude database on small, high-bypass ratio engine performance and operability. In particular, the program documents the impact of altitude (Reynolds Number) on the aero-performance of the low-pressure turbine (fan turbine). A second objective was to assess the ability of a state-of-the-art CFD code to predict the effect of Reynolds number on the efficiency of the low-pressure turbine. CFD simulation performed prior and after the engine tests will be presented and discussed. Key findings are the ability of a state-of-the art CFD code to accurately predict the impact of Reynolds Number on the efficiency and flow capacity of the low-pressure turbine. In addition the CFD simulations showed the turbulent intensity exiting the low-pressure turbine to be high (9%). The level is consistent with measurements taken within an engine.

Castner, Raymond↗
NASA NTRS1983

An assessment of the use of antimisting fuel in turbofan engines

An evaluation was made on the effects of using antimisting kerosene (AMK) on the performance of the components from the fuel system and the combustor of current in service JT8D aircraft engines. The objectives were to identify if there were any problems associated with using antimisting kerosene and to determine the extent of shearing or degradation required to allow the engine components to achieve satisfactory operation. The program consisted of a literature survey and a test program which evaluated the antimisting kerosene fuel in laboratory and bench component testing, and assessed the performance of the combustor in a high pressure facility and in an altitude relight/cold ignition facility.

Fiorentino, A. J.↗
NASA NTRSDate not supplied

Automatic Generation of Guard-Stable Floating-Point Code

In floating-point programs, test instability occurs when the control flow of a conditional statement diverges from its ideal execution under real arithmetic. This phenomenon is caused by the presence of round-off errors in floating-point computations. Writing programs that correctly handle test instability often require expertise on finite precision computations and rounding errors. This paper presents a fully automatic tool chain that generates and formally verifies a test-stable floating-point C program from its functional specification in real arithmetic. The generated program is instrumented to soundly detect when unstable tests may occur and, in these cases, to issue a warning. The proposed approach combines the PRECiSA floating-point static analyzer, the Frama-C software verification suite, and the PVS theorem prover.

Floating-Point Arithmetic↗
NASA NTRS1975

Experimental study of transient liquid motion in orbiting spacecraft

The results are presented of a twofold study of transient liquid motion such as that which will be experienced during orbital maneuvers by space tug. A test program was conducted in a low-g test facility involving twenty-two drops. Biaxial, low-g accelerations were applied to an instrumented, model propellant tank during free-fall testing, and forces exerted during liquid reorientation were measured and recorded. Photographic records of the liquid reorientation were also made. The test data were used to verify a mechanical analog which portrays the liquid as a point mass moving on an ellipsoidal constraint surface. The mechanical analog was coded into a FORTRAN IV digital computer program: LAMPS, Large AMPlitude Slosh. Test/analytical correlation indicates that the mechanical analog is capable of predicting the overall force trends measured during testing.

Berry, R. L.↗
NASA NTRS1965

Space vacuum investigations

Inaccessible-Non Repairable- Costly: The meaning of these words is absolute in the event of a complete failure of an orbiting spacecraft. Adequate design, or rather, minimizing chance of failure, challenges all scientists and engineers. Where experience has not been developed, the risk involved in a new application must be weighed against the consequence of a design failure. In space work, the spectrum of consequence is extremely wide. It ranges from loss of scientific data on one hand, to loss of life on the other.. There is little question that knowledge of the space environment and its effects must be determined to produce reliable spacecraft. Tests to prove the design must be performed with equipment capable of simulating the effects of the environment in which the design is to operate. This does not necessarily mean that the natural environment must be duplicated. The degree of environmental simulation that should be achieved depends primarily upon the significance of the physical effects it causes. The purpose of space vacuum simulation in an environmental test program should be accurately conceived and the testing phased to obtain maximum information from the limited samples available for test. This discussion is confined to some of the factors involved in simulating the effects of space vacuum environment. This survey is by no means complete, but will touch on some of the highlights in this field: 1. A description of the environment 2. The level of simulation necessary to evaluate its effects 3. Test equipment capability 4. Experience in test 5. Experience in orbit 6. Observations & future emphasis

VACUUM EFFECT↗
NASA NTRS1972

Apollo experience report: Very high frequency ranging system

The history of the Apollo very-high-frequency ranging system development program is presented from the program-planning stage through the final-test and flight-evaluation stages. Block diagrams of the equipment are presented, and a description of the theory of operation is outlined. A sample of the distribution of errors measured in the aircraft-flight test program is included. The report is concluded with guidelines or recommendations for the management of development programs having the same general constraints.

Panter, W. C.↗
NASA NTRS1972

Frangible glass canisters

The need for a canister that can release its contents without disturbing the contents dynamically is discussed. The solution of this problem by the use of a frangible glass canister is considered. The basic theory applicable to frangible glass and the method of initiating a command flaw are discussed. A brief description of the test program and the results of a flight test are presented.

Seifert, R.↗
NASA NTRS1972

Characterization of the space shuttle reaction control system engine

A computer program was developed and written in FORTRAN 5 which predicts the transient and steady state performance and heat transfer characteristics of a pulsing GO2/GH2 rocket engine. This program predicts the dynamic flow and ignition characteristics which, when combined in a quasi-steady state manner with the combustion and mixing analysis program, will provide the thrust and specific impulse of the engine as a function of time. The program also predicts the transient and steady state heat transfer characteristics of the engine using various cooling concepts. The computer program, test case, and documentation are presented. The program is applicable to any system capable of utilizing the FORTRAN 4 or FORTRAN 5 language.

Wilson, M. S.↗
NASA NTRS1974

A study of relationships between performance in system tests and space

Approaches for measuring the effectiveness of tests and test programs are considered, taking into account system test effectiveness, thermal-vacuum test effectiveness, and vibration test effectiveness. Methods for predicting space performance on the basis of system test effectiveness are discussed along with aspects of defect detection in thermal-vacuum tests. Questions regarding the thermal-vacuum test costs in relation to the probability of early space failures are also explored.

Timmins, A. R.↗
NASA NTRS1975

Viking 1975 Orbiter Development Test Model/Lander Dynamic Test Model - Dynamic environmental testing

An overview is presented of the dynamic environmental test program for the Viking 1975 Orbiter Development Test Model/Lander Dynamic Test Model. The spacecraft and its systems are described, and the test methods are discussed in detail. Tests described include the modal survey, the forced-vibration test, and the acoustic test. It is shown that the modal testing provided a good correlation with analytical predictions and that all the major structural loads were found to be below 50 Hz.

Milder, G.↗
NASA NTRS1977

F-16 flutter model studies with external wing stores

The flutter prevention and clearance task for the F-16 airplane is being accomplished in a combined analysis, wind-tunnel dynamic model test, and flight flutter test program. This paper presents highlight results from transonic flutter model studies. The flutter model was constructed to support the flutter prevention and clearance program from preliminary design through flight flutter tests. The model tests were conducted in NASA's Langley Transonic Dynamics Tunnel. The large full-span free-flying model is shown to be an effective tool in defining airplane flutter characteristics by demonstrating freedom from flutter for most configurations and by defining optimum solutions for a few troublesome configurations.

Foughner, J. T., Jr.↗
NASA NTRS1977

Design and Development of the Space Shuttle Tail Service Masts

The successful launch of a space shuttle vehicle depends on the proper operation of two tail service masts (TSMs). Reliable TSM operation is assured through a comprehensive design, development, and testing program. The results of the concept verification test (CVT) and the resulting impact on prototype TSM design are presented. The design criteria are outlined, and the proposed prototype TSM tests are described.

Dandage, S. R.↗
NASA NTRS1979

A summary of NASA/Air Force full scale engine research programs using the F100 engine

A full scale engine research (FSER) program conducted with the F100 engine is presented. The program mechanism is described and the F100 test vehicles utilized are illustrated. Technology items were addressed in the areas of swirl augmentation, flutter phenomenon, advanced electronic control logic theory, strain gage technology and distortion sensitivity. The associated test programs are described. The FSER approach utilizes existing state of the art engine hardware to evaluate advanced technology concepts and problem areas. Aerodynamic phenomenon previously not considered by design systems were identified and incorporated into industry design tools.

Deskin, W. J.↗