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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 343 records · Page 19

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NASA NTRS1984

Commercial launch vehicles and upper stages

Since the beginning of the space age in October 1957, a family of expendable launch vehicles, capable of launching a wide range of payloads, was developed along with the Space Shuttle and a number of upper stages. A brief description is presented of selected orbits which have proved to be most useful for initial or conceptual understanding of space operations, taking into account direct injection and Hohman transfers, and synchronous and sun-synchronous orbits. Early American boosters are discussed along with current expendable launch vehicles, giving attention to the Vanguard, Redstone and Juno, Saturn 1B and Saturn V, Scout, the Atlas booster, Atlas Centaur, Delta, Titan IIIC, and Ariane. Details regarding the Space Shuttle are considered along with PAM-D, PAM-A, PAM-DII, TOS, IUS, Centaur-G, and Syncom-IV and Intelsat-VI.

Mahon, J.↗

NASA NTRS1982

Computer program for post-flight analysis of rigid body moments acting on a launch vehicle first stage

A FORTRAN coded computer program and method for evaluation of the rigid body disturbing moments for a launch vehicle first stage based on post-flight measurements is described. The technique is a straightforward deterministic approach. Residual moments are computed to satisfy the equations of motion. Residuals are expressed in terms of altered vehicle characteristics; the aerodynamic coefficients, thrust misalignment, and control effectiveness. This method was used on the Scout launch vehicle and uncovered several significant differences between flight data and wind tunnel data. The computer program is written in FORTRAN IV for a CDC CYBER 173 computer system.

Knauber, R. N.↗

NASA NTRS1982

Computer program for post-flight evaluation of a launch vehicle upper-stage on-off reaction control system

This report describes a FORTRAN IV coded computer program for post-flight evaluation of a launch vehicle upper stage on-off reaction control system. Aerodynamic and thrust misalignment disturbances are computed as well as the total disturbing moments in pitch, yaw, and roll. Effective thrust misalignment angle time histories of the rocket booster motor are calculated. Disturbing moments are integrated and used to estimate the required control system total inpulse. Effective control system specific inpulse is computed for the boost and coast phases using measured control fuel useage. This method has been used for more than fifteen years for analyzing the NASA Scout launch vehicle second and third-stage reaction control system performance. The computer program is set up in FORTRAN IV for a CDC CYBER 175 system. With slight modification it can be used on other machines having a FORTRAN compiler. The program has optional CALCOMP plotting output. With this option the program requires 19K words of memory and has 786 cards. Running time on a CDC CYBER 175 system is less than three (3) seconds for a typical problem.

Knauber, R. N.↗

NASA NTRS1985

Feasibility study for ergonomic analysis and design of future helicopter cockpit systems

The Army's light scout-attack helicopters (LHXs), planned for deployment in the 1990's, will fly nap-of-the-earth (NOE) missions in high threat environments, often under poor visibility and adverse atmospheric conditions, and probably with a one man crew. A procedure for the analysis of pilot workload that will identify and explicate the main characteristics of those LHX mission components holding overload potential is described. A principled, in-depth, explication of the cognitive demans of LHX piloting is essential to any effective effort to address the human factors issues. A task-analytic procedure that will yield the detail and organizstion needed to achieve these goals is examined.

Hawkins, H. L.↗

NASA NTRS1986

Investigation of crew performance in a multi-vehicle supervisory control task

Crew information processing and decision making in a supervisory control task which is loosely based on the mission of future generation helicopters is measured and represented. Subjects control the motion and activities of their own vehicle and direct the activities of four additional craft. The task involves searching an uncertain environment for cargo and enemies, returning cargo to home base and destroying enemies while attempting to avoid destruction of the scout and the supervised vehicles. A series of experiments with two-person crews and one-person crews were performed. Resulting crew performance was modeled with the objective of describing and understanding the information processing strategies utilized. Of particular interest are problem simplification strategies under time stress and high work load, simplification and compensation in the one-person cases, crew coordination in the two-person cases, and the relationship between strategy and errors in all cases. The results should provide some insight into the effective use of aids, particularly aids based on artificial intelligence, for similar tasks. The simulation is described which is used for the study and some preliminary results from the first two-person crew study are discussed.

Miller, R. A.↗

NASA NTRS1987

Description of the US Army small-scale 2-meter rotor test system

A small-scale powered rotor model was designed for use as a research tool in the exploratory testing of rotors and helicopter models. The model, which consists of a 29 hp rotor drive system, a four-blade fully articulated rotor, and a fuselage, was designed to be simple to operate and maintain in wind tunnels of moderate size and complexity. Two six-component strain-gauge balances are used to provide independent measurement of the rotor and fuselage aerodynamic loads. Commercially available standardized hardware and equipment were used to the maximum extent possible, and specialized parts were designed so that they could be fabricated by normal methods without using highly specialized tooling. The model was used in a hover test of three rotors having different planforms and in a forward flight investigation of a 21-percent-scale model of a U.S. Army scout helicopter equipped with a mast-mounted sight.

Phelps, Arthur E., III↗

NASA NTRS1986

Guidance automation for nap-of-the-earth flight

Low-Altitude/Nap-of-the-Earth (NOE) rotorcraft flight in adverse weather has been identified as a major technology void by both military and civil agencies because of its direct relationship to the needs of the military's new scout-attack helicopter and to various civilian applications including Emergency Medical Services (EMS). As part of NASA's Aircraft Automation Program, Ames Research Center has identified as a major goal the automating and advancing of applicable terrain following/terrain avoidance/obstacle avoidance (TF/TA/OA) guidance technologies to a level where NOE rotorcraft flight can be demonstrated in an advanced simulator and, later, in fully automatic flight. Areas of emphasis to date for achieving automatic guidance include real-time sensor blending and the real-time computation of NOE guidance commands. The present paper reports on the guidance command generation. The applicability of TF/TA techniques to the NOE problem is described, and simulation results are presented that suggest that automatic NOE can indeed be accomplished.

Denton, Richard V.↗

NASA NTRS1983

Impact of flying qualities on mission effectiveness for helicopter air combat, volume 1

A computer simulation to investigate the impact of flying qualities on mission effectiveness is described. The objective of the study was to relate the effects of flying qualities, such as precision of flight path control and pilot workload, to the ability of a single Scout helicopter, or helicopter team, to accomplish a specified anti-armor mission successfully. The model of the actual engagement is a Monte Carlo simulation that has the capability to assess the effects of helicopter characteristics, numbers, tactics and weaponization on the force's ability to accomplish a specific mission against a specified threat as a function of realistic tactical factors. A key feature of this program is a simulation of micro-terrain features and their effects on detection, exposure, and masking for nap-of-the-earth (NOE) flight.

Harris, T. M.↗

NASA NTRS1987

Future plans for the NASA suborbital program

The development of more reliable heavy-lift balloons and a fine pointed gondola; the development of the Black Brant-12 rocket for auroral research; and the development of a collaborative Orbiting Payload Using Scout program are outlined. Through 1989 NASA will conduct a comprehensive program of aircraft, balloon, and rocket campaigns in conjunction with Shuttle and satellite measurements on the Supernovae 1987a.

Shawhan, S. D.↗

NASA NTRS1987

A comparison of one- and two-person crew performance in a supervisory control task

One- and two-person crews performed a simulated supervisory control task in which they had to directly control a scout helicopter and indirectly control four friendly helicopters in a hostile environment. One-person crews relied on an autopilot more than two-person crews in order to deal with multiple task demands. However, two-person crews were superior in terms of overall performance, and on particular subtasks such as searching for cargo and enemy craft and destroying enemy craft after they were located.

Miller, R. Allen↗

NASA NTRS1988

Attitude motion of a non-attitude-controlled cylindrical satellite

In 1985, two non-attitude-controlled satellites were each placed in a low earth orbit by the Scout Launch Vehicle. The satellites were cylindrical in shape and contained reservoirs of hydrazine fuel. Three-axis magnetometer measurements, telemetered in real time, were used to derive the attitude motion of each satellite. Algorithms are generated to deduce possible orientations (and magnitudes) of each vehicle's angular momentum for each telemetry contact. To resolve ambiguities at each contact, a force model was derived to simulate the significant long-term effects of magnetic, gravity gradient, and aerodynamic torques on the angular momentum of the vehicles. The histories of the orientation and magnitude of the angular momentum are illustrated.

Wilkinson, C. K.↗

NASA NTRS1988

NASA future missions

The NASA astrophysics programs are outlined. The Hubble Space Telescope; the infrared background explorer, COBE; the Shuttle-based Astro-1/BBXRT UV and X-ray experiments; the extreme ultraviolet explorer, EUVE, the diffuse X-ray experiment, DXS, and the Gamma Ray Observatory, are described, and NASA involvement in ROSAT, exploring the X-ray sky, and ORFEUS, exploring the UV sky, is shown; SCOUT-class explorers are mentioned. Suborbital science obtained from aircraft and rockets will continue and expand; supporting research and technology will also continue and substantial effort will be expended on improvement of data systems to promote data accessibility and ease of use.

Pellerin, Charles J.↗

NASA NTRS1988

Space transportation - Options and opportunities

The development space transportation options to earth orbit and beyond are summarized. The performance of available launch systems is reviewed, including the Scout, Delta, Long March 3, Atlas Centaur, Ariane 3, Titan 34D, Proton, the Japanese M-3S-II, N-1, and H-1, and the Space Shuttle. Launch vehicle which are planned or are under development are examined, including the Conestoga, Industrial Launch Vehicle, Titan II, Delta II, H-II, Ariane 5, Titan IV, and the NASA/DOD Heavy Lift Launch Vehicle. Also, issues pertinent to the development of space transportation vehicles are considered, such as reliability, reduced unit cost, reduced lead time, and improved payload accommodations.

Loftus, J. P., Jr.↗

NASA NTRS1990

Articulated Suspension Without Springs

Wheels negotiate bumps and holes with minimal tilting of vehicle body. In new suspension, wheel climbs obstacle as high as 1 1/2 times its diameter without excessive tilting of chassis. Provides highly stable ride over rough ground for such vehicles as wheelchairs, military scout cars, and police and fire robots. System of levers distributes weight to wheels. Sized to distribute equal or other desired portions of load among wheels.

Bickler, Donald B.↗

NASA NTRS1989

United States space transportation survey

Different developmental paths for the U.S. space transportation fleet are discussed. Development of a purely cargo, unmanned space shuttle, using many components of the present manned space shuttle system, is presented. Future manned spacecraft solutions are discussed. Launch vehicle programs for unmanned missions are described. The Titan solid rocket motor upgrade is identified as the biggest improvement in this area. A return to a better balance between manned and unmanned launch systems for space transportation is predicted. The Titan, Delta, Scout, and Pegasus families of rockets are described. The need to upgrade this fleet in meeting the space challenges of the future is stressed.

Branscome, Darrel R.↗

NASA NTRS1991

Feasibility of solar power for Mars

NASA, through Project Pathfinder, has put in place an advanced technology program to address future needs of manned space exploration. Included in the missions under study is the establishment of outposts on the surface of Mars. The Surface Power program in Pathfinder is aimed at providing photovoltaic array technology for such an application (as well as for the lunar surface). Another important application is for unmanned precursor missions, such as the photovoltaic-power aircraft, which will scout landing sites and investigate Mars geology for a 1 to 2 year mission without landing on the surface. Effective design and utilization of solar energy depend to a large extent on adequate knowledge of solar radiation characteristics in the region of solar energy system operation. The two major climatic components needed for photovoltaic system designs are the distributions of solar insolation and ambient temperature. These distributions for the Martian climate are given at the two Viking lander locations but can also be used, to the first approximation, for other latitudes. One of the most important results is that there is a large diffuse component of the insolation, even at high optical depth, so that solar energy system operation is still possible. If the power system is to continue to generate power even on high optical opacity days, it is thus important that the photovoltaic system be designed to collect diffuse irradiance as well as direct. In absence of long term insolation and temperature data for Mars, the data presented can be used until updated data are available. The ambient temperature data are given as measured directly by the temperature sensor; the insolation data are calculated from optical depth measurements of the atmosphere.

Appelbaum, Joseph↗

NASA NTRS1991

Next generation: Unmanned launch vehicles and upper stages: The needs

The focus is on common vehicle elements, higher mission success, and lower transportation cost with respect to the common needs of the Department of Defense, NASA, and U.S. Industry. The following are presented in viewgraph form: (1) perspectives on mission costs and failures; (2) the recurring costs of the Delta 7925, Atlas/Centar, Titan 3, and Titan 4; (3) U.S. launches from 1957-1987 of Vanguard, Jupiter, Thor/Delta, Juno, Atlas, Scout, Redstone, Saturn, Titan, and the Space Transportation System; and (4) subsystem sources of failure. The following topics are also briefly presented: (1) engine costs; (2) a summary of flight experience; (3) recommendations for next generation space transportation; (4) low cost engine demonstration; and (5) the next generation commercial expendable launch vehicle (ELV) needs estimate.

Gunn, Charles R.↗

NASA NTRS1992

High-Clearance Six-Wheel Suspension

Multilevered suspension system gives body of vehicle high clearance and allows wheels to be steered independently. Suspension linkages above wheels enable body to skim over obstacles as high as wheel. Levers and independently steered wheels enable vehicle to climb steps 1 1/2 wheel diameters high and cross gaps 1 3/4 wide. Adaptable to off-the-road recreational vehicles, military scout vehicles, and robotic emergency vehicles.

Bickler, Donald B.↗