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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 559 records · Page 31

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NASA NTRS1988

Fuel-optimal trajectories for aeroassisted coplanar orbital transfer problem

The optimal-control problem arising in coplanar orbital transfer using aeroassist technology is addressed. The maneuver involves the transfer from high earth orbit to low earth orbit with minimum fuel consumption. Simulations are carried out to obtain a corridor of entry conditions which are suitable for flying the spacecraft through the atmosphere. A highlight of the present work is the application of an efficient multiple shooting method for handling the difficult nonlinear two-point boundary value problem resulting from the optimization procedure.

Naidu, D. S.↗

NASA NTRS1988

Spacelab 2 Upper Atmospheric Modification experiment over Arecibo. I - Neutral gas dynamics

The Orbital Maneuvering Subsystem engines of the Space Shuttle were used to inject H2, CO2, H2O and other combustion products into the upper atmosphere over the Arecibo Observatory. Images of the airglow enhancements that resulted from chemical reactions between the exhaust gases and the F-layer plasma showed that the exhaust vapor trail came to rest 80 km downstream from the center of the burn. A computer simulation of the gas dynamics shows that the region of the burn was dominated by a 'snow plow' effect sweeping out a corridor in the atmosphere and collisionally heating the injected vapors.

Bernhardt, P. A.↗

NASA NTRS1989

Transport of ions injected by AMPTE magnetotail releases

The BA and Li ions released in the magnetotail by the AMPTE IRM satellite were not observed in the inner magnetosphere with the AMPTE CCE satellite. In an effort to understand these results, Cladis and Francis (1988) modeled the expansion and ionization of the released atoms and computed several hundred guiding-center trajectories of the ions to sample the motion of each ion cloud. Here, the transport calculations are improved, principally by computing the full gyration motion of the ions in a more realistic model of the geomagnetic tail. The results indicate that the Ba(+) ions were convected inward along a narrow corridor, which was at least 2 earth radii away from the satellite in the case of the first Ba release and at least 3 earth radii away in the case of the second Ba release. Even if the ions had reached the satellite, their energies would have been too low to be detected. The Li(+) ions from both releases drifted inward over broad regions which overlapped the satellite in space and time. However, their fluxes at the satellite were somewhat too low to be detected.

Cladis, J. B.↗

NASA NTRS1988

A look at tomorrow's civil tiltrotor

The present evaluation of the development status of the tilt-rotor VTOL aircraft concept proceeds to identify a large civilian market potential for vehicles of this type, especially along high commuter traffic density urban corridors. A variant of the V-22 tilt-rotor is judged to be of sufficient size for this high-density passenger market in the near term, provided that the rotor-drive system undergoes suitable modifications for more reliable one-engine-inoperative emergency operation. New, larger-than-V-22 and least-cost-optimized civil tilt-rotors carrying as many as 75 passengers are under study, but will require the construction of 'vertiports' at strategically advantageous urban locations.

Wilkerson, Joseph B.↗

NASA NTRS1990

Rolling Robot

Proposed rolling robot routinely traverses rough terrain, clearing rocks as high as 1 m. Climbs steps 1 m high and spans ditches 2.3 m wide. Simple but rugged semiautonomous rover has large wheels and articulated body. With combined yaw, roll, and four-wheel drive, robot crawls slowly to pass over soft or sandy terrain. Senses terrain along corridor, chooses path to avoid insurmountable obstacles, and monitors state of vehicle for unexpected hazards.

Larimer, Stanley J.↗

NASA NTRS1990

En route noise annoyance laboratory test: Preliminary results

Until recently concerns about the impact of aircraft noise on people have centered around the takeoff and landing operations of aircraft in the vicinity of airport terminals. The development of the advanced turboprop (propfan) engine, modifications to air corridors, and the desire to maintain a natural environment in national parks and recreation areas have now focused attention on the impact at ground level of the en route noise produced by aircraft at cruise conditions and altitudes. Compared to terminal area noise, en route noise is characterized by relatively low noise levels, lack of high frequency spectral content, and long durations. Much research has been directed towards understanding and quantifying the annoyance caused by terminal area aircraft noise, but relatively little research has been conducted for en route noise. To address this need, a laboratory experiment was conducted to quantify the annoyance of people on the ground to en route noise generated by aircraft at cruise conditions. The objectives of the experiment are to determine the annoyance prediction ability of noise measurement procedures and corrections when applied to en route noise; to determine differences in annoyance response to en route noise and takeoff/landing noise; and to determine differences in annoyance response to advanced turboprop en route noise and conventional jet en route noise.

Mccurdy, David A.↗

NASA NTRS1990

The effect of interplanetary trajectory options on a manned Mars aerobrake configuration

Manned Mars missions originating in low Earth orbit (LEO) in the time frame 2010 to 2025 were analyzed to identify preferred mission opportunities and their associated vehicle and trajectory characteristics. Interplanetary and Mars atmospheric trajectory options were examined under the constraints of an initial manned exploration scenario. Two chemically propelled vehicle options were considered: (1) an all propulsive configuration, and (2) a configuration which employs aerobraking at Earth and Mars with low lift/drag (L/D) shapes. Both the interplanetary trajectory options as well as the Mars atmospheric passage are addressed to provide a coupled trajectory simulation. Direct and Venus swingby interplanetary transfers with a 60 day Mars stopover are considered. The range and variation in both Earth and Mars entry velocity are also defined. Two promising mission strategies emerged from the study: (1) a 1.0 to 2.0 year Venus swingby mission, and (2) a 2.0 to 2.5 year direct mission. Through careful trajectory selection, 11 mission opportunities are identified in which the Mars entry velocity is between 6 and 10 km/sec and Earth entry velocity ranges from 11.5 to 12.5 km/sec. Simulation of the Earth return aerobraking maneuver is not performed. It is shown that a low L/D configuration is not feasible for Mars aerobraking without substantial improvements in the interplanetary navigation system. However, even with an advanced navigation system, entry corridor and aerothermal requirements restrict the number of potential mission opportunities. It is also shown that for a large blunt Mars aerobrake configuration, the effects of radiative heating can be significant at entry velocities as low as 6.2 km/sec and will grow to dominate the aerothermal environment at entry velocities above 8.5 km/sec. Despite the additional system complexity associated with an aerobraking vehicle, the use of aerobraking was shown to significantly lower the required initial LEO weight. In comparison with an all propulsive mission, savings between 19 and 59 percent were obtained depending upon launch date.

Braun, Robert D.↗

NASA NTRS1990

A simplified ring-vortex downburst model

Three dimensional incompressible vortex rings are used to model downburst flow field, and modifications are made to express the induced velocities analytically. As a result, this three dimensional downburst model can be used in trajectory optimization, as well as in flight simulations. Two such vortex rings are superposed to match the JAWS AB Corridor wind profiles and the DFW Downburst wind profiles. Model parameters are determined through nonlinear least square fit.

Zhao, Yiyuan↗

NASA NTRS1990

Earth atmospheric entry studies for manned Mars missions

Decelerations, heating rates, and total heat loads encountered when returning from Mars to earth at entry speeds of 12 km/sec to 16 km/sec are studied. For entry at 14 km/sec, it is found that a lift/drag ratio (L/D) of 0.5 is required to provide a guidance corridor margin near 1 deg for the specified deceleration limit of 5 g. For a blunted, raked cone with an L/D = 0.5, the peak heating rate near the aft end of the forebody varies from 0.14 to 0.23 kW/sq cm for laminar flow. If ablation triggers boundary layer transition, the peak heating can rise to 0.5 or up to 0.72 kW/sq cm. All heating rates are sufficiently high to make ablative heat shields necessary.

Tauber, M. E.↗

NASA NTRS1990

Atmospheric effects on Martian aerocapture

A preliminary study of the effects of the atmosphere on Martian aerocapture has been completed at NASA-Johnson. Nominal cases were defined and several types of density dispersions utilized to show the effect of L/D ratio on aerocapture performance. Both open and closed loop three-degree-of-freedom simulations were developed. The open loop work demonstrated the reduction of the aerocapture corridor in the presence of density biases and shears. Closed loop runs were studied in the presence of shear-biases where the aerocapture trajectory was divided into three regions or phases. Each phase independently had a nominal density or a dispersed + 100 percent density. Two phase combinations were found to cause aerocapture failures with the three L/Ds considered: 0.3, 0.7, 1.0. There is a significant improvement in aerocapture performance as the L/D is increased from 0.3 to 0.7, but a much smaller increase in performance as the L/D is increased from 0.7 to 1.0. Based on current knowledge of the Martian atmosphere, a minimum L/D of 0.7 is recommended for early Mars missions.

Ess, Robert H.↗

NASA NTRS1991

Civil tiltrotor missions and applications. Phase 2: The commercial passenger market

The commercial passenger market for the civil tiltrotor was examined in phase 2. A market responsive commercial tiltrotor was found to be technically feasible, and a significant worldwide market potential was found to exist for such an aircraft, especially for relieving congestion in urban area-to-urban area service and for providing cost effective hub airport feeder service. Potential technical obstacles of community noise, vertiport area navigation, surveillance, and control, and the pilot/aircraft interface were determined to be surmountable. Nontechnical obstacles relating to national commitment and leadership and development of ground and air infrastructure were determined to be more difficult to resolve; an innovative public/private partnership is suggested to allow coordinated development of an initial commercial tiltrotor network to relieve congestion in the crowded US Northeast corridor by the year 2000.

Thompson, P.↗

NASA NTRS1990

Integrated imaging experiment with C-SAR and other geological image data across the Nelson Front, Northern Manitoba

This paper presents preliminary results from the integration of geophysical and geological data sets using Bayesian statistical analysis with the purpose of mapping the Churchill-Superior Boundary zone. In the Wabowden area the contribution of each rock type to the aeromagnetic anomaly is judged by convolving the aeromagnetic anomaly value with the average magnetic susceptibility. The 'a posteriori' probabilities of significant patterns in the new data are then computed. The highest 'a posteriori' probability occurs along a narrow corridor whose trend coincides remarkably with the location of the Churchill-Superior Boundary Zone. In the Wekusko Lake area, C-SAR and TM data were integrated using an image analysis system. Here the emphasis is on mapping of geological structures.

Rao, G. S. K.↗

NASA NTRS1989

A comparison of two exceptional snowstorms during the early 20th century

Two East-Coast snowstorms of the early twentieth century, which generated massive accumulations over portions of the Atlantic coastal plain, are described. The 'Christmas Storm' of December 25-26, 1909 produced snowfalls of greater than 25 cm over most of the Northeast Corridor from Maryland to southern New England, while the 'Knickerbocker Storm' of January 27-29, 1922 produced a total of 71 cm at Washington, DC. The storms are examined by constructing surface-weather analyses based on original data; surface observations for the continental United States at 0100 and 1300 UTC are obtained from the National Climatic Data Center (NCDC), ship reports from American vessels are taken from the NCDC archives, and the 1300 UTC data is supplemented by Canadian observations and European ship reports. In spite of the vast differences in the evolutions of the storms, it is found that both produced similarly massive snowfalls, therefore, it is concluded that a wide range of synoptic conditions can give rise to major snowstorms along the East Coast.

Weiss, Alan D.↗

NASA NTRS1991

Earth return aerocapture for manned Mars missions

Lift to drag ratio (L/D) requirements and stagnation point heating have been examined for a variety of probable entry conditions and vehicle configurations. It is found that vehicles with an L/D of 0.5 or more provide a corridor width of at least 0.7 degrees while keeping the peak deceleration load below 5 g for approach velocities up to 14.5 km/s. It is shown that stagnation point peak heating rates and integrated heat load critically depend on both entry velocity and ballistic coefficient. For the most severe cases under consideration, peak heating and integrated heat load are five times greater than those encountered by Apollo but within the range of experience for unmanned vehicles.

Tauber, M. E.↗

NASA NTRS1991

Earth aerobraking strategies for manned return from Mars

The atmospheric flight environment of manned return from Mars is evaluated by analyzing the earth-return entry corridor. To identify and quantify the effects of various atmospheric exit conditions on the mission, the differences beween the capture to a specific orbit and the direct entry to a target splashdown site are investigated. The differences are quantified in terms of the airbrake lift-drag ratio requirements, the stagnation-point heating, and the significance of off-nominal atmospheric conditions. Results are presented on three different earth-return aerobraking scenarios: (1) the capture into a phasing orbit with a 24-hr period, (2) the capture into a 500-km circular orbit, and (3) the direct entry to splashdown.

Braun, Robert D.↗

NASA NTRS1991

Comment on 'The Space Shuttle's impact on the stratosphere' by Michael J. Prather et al

Prather et al. (1990) argued that no local hole in column ozone could occur above the launch site of the Space Shuttle because (1) the HCl in the exhaust would require some time to be converted into more catalytically active forms, (2) the Shuttle trajectory is not vertically aligned, and (3) the corridor of exhaust gases is laterally spread over more than 1000 km in a day. In contradiction to these arguments, it is maintained here that assumption (1) is inconsistent with the empirical evidence, rendering (2) and (3) insufficient to maintain the claim that no local hole in column ozone could occur. In a reply, ozone image data from the TOMS on Nimbus 7 is used to support the argument of Prather et al.

Aftergood, Steven↗

NASA NTRS1991

Mars entry-to-landing trajectory optimization and closed loop guidance

The guidance strategy of the Mars Rover Sample Return mission is presented in detail. Aeromaneuver versus aerobrake trades are examined, and an aerobrake analysis is presented which takes into account targeting, guidance, flight control, trajectory profile, delivery accuracy. An aeromaneuver analysis is given which includes the entry corridor, maneuver footprint, guidance, preentry phase, constant drag phase, equilibrium guide phase, variable drag phase, influence of trajectory profile on the entry flight loads, parachute deployment conditions and strategies, and landing accuracy. The Mars terminal descent phase is analyzed.

Ilgen, Marc R.↗

NASA NTRS1993

Light-Flash Wind-Direction Indicator

Proposed wind-direction indicator read easily by distant observers. Indicator emits bright flashes of light separated by interval of time proportional to angle between true north and direction from which wind blowing. Timing of flashes indicates direction of wind. Flashes, from high-intensity stroboscopic lights seen by viewers at distances up to 5 miles or more. Also seen more easily through rain and fog. Indicator self-contained, requiring no connections to other equipment. Power demand satisfied by battery or solar power or both. Set up quickly to provide local surface-wind data for aircraft pilots during landing or hovering, for safety officers establishing hazard zones and safety corridors during handling of toxic materials, for foresters and firefighters conducting controlled burns, and for real-time wind observations during any of variety of wind-sensitive operations.

Zysko, Jan A.↗