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  • Polymer and Materials Science  (3,309)
  • 42.75
  • NAVIGATION
  • 1970-1974  (2,262)
  • 1960-1964  (1,329)
  • 1971  (2,262)
  • 1962  (1,329)
Collection
Keywords
Publisher
Years
  • 1970-1974  (2,262)
  • 1960-1964  (1,329)
Year
  • 1
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    Drag-free satellite control system technology (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Some of the technology developed in building a drag-free satellite simulator for laboratory use is described. The design decisions made in order to achieve a 10 to the -11th power g perturbation level for the navigation satellite is discussed. The control system development that will make possible drag-free operation of spinning satellites to reduce perturbation levels by averaging is described.
    Keywords: NAVIGATION
    Type: JPL Proc. of the Conf. on Exptl. Tests of Gravitation Theories; p 190-196
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  • 2
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    Experiment D010: Ion sensing attitude control (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The feasibility of an attitude control system that uses environmental positive ions and an electrostatic detection system to measure spacecraft pitch and yaw is studied. The secondary objective was to measure the spatial and temporal variations of ambient positively charged particles along the orbital path of the Gemini 10 and 12 spacecrafts. The results proved that the use of a horizon detector in conjunction with pitch and yaw sensors would facilitate complete description of the spacecraft position and attitude. Furthermore, with the addition of a servosystem, the unit could be used as a complete automatic attitude-control system that would be applicable from the lowest satellite altitudes up to at least 10 earth radii. Also, results established that the charge density along the trajectory of the satellite could be determined by transmission of output voltages from the individual electrometers.
    Keywords: NAVIGATION
    Type: NASA. Manned Spacecraft Center The Gemini Program: Phys. Sci. Expt. Sum.; p 199-213
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  • 3
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    Experiment T002: Manual navigation sightings (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Navigation-type measurements through the window of the stabilized Gemini 12 spacecraft by the use of a hand-held sextant are reported. The major objectives were as follows: (1) to evaluate the ability of the crewmen to make accurate navigational measurements by the use of simple instruments in an authentic space flight environment; (2) to evaluate the operational feasibility of the measurement techniques by the use of the pressure suit with the helmet off and with the helmet on and the visor closed; (3) to evaluate operational problems associated with the spacecraft environment; and (4) to validate ground based simulation techniques by comparison of the inflight results with base line data obtained by the pilot by the use of simulators and celestial targets from ground based observatories.
    Keywords: NAVIGATION
    Type: The Gemini Program: Phys. Sci. Expt. Sum.; p 61-69
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  • 4
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    Future Possibilities in spacecraft ranging and Doppler systems (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The structure of spacecraft tracking radar, and range and Doppler measurements, are discussed. Ranging can be used in conjunction with Doppler to determine the total number of charged particles on the radio path. Ranging can also be employed as the primary data type in determining certain kinds of orbits. The basic configuration of the ranging and Doppler system is considered. Inherent limitations on its accuracy with respect to the oscillator, transponder, ground equipment, signal to noise ratio, and general operation are noted.
    Keywords: NAVIGATION
    Type: Proc. of the Conf. on Exptl. Tests of Gravitation Theories; p 166-177
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  • 5
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    Experiment D005: Star occultation navigation (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The usefulness of star occultation measurements for space navigation and the determination of a horizon density profile which could be used to update atmospheric models for horizon-based measurement systems were studied. The time of occultation of a known star by a celestial body, as seen by an orbiting observer, determines a cylinder of position, the axis of which is the line through the star and the body center, and the radius of which is equal to the occulting-body radius. The dimming percentage, with respect to the altitude of this grazing ray from the star to the observer, is a percentage altitude for occultation. That is, the star can be assumed to be occulted when it reaches a predetermined percentage of its unattenuated value. The procedure used was to measure this attenuation with respect to time to determine the usefulness of the measurements for autonomous space navigation. In this experiment, the crewmembers had to accomplish star acquisition, identification, calibration, and tracking. Instrumentation was required only for measurement of the relative intensity of the star as it set into the atmosphere.
    Keywords: NAVIGATION
    Type: NASA. Manned Spacecraft Center The Gemini Program: Phys. Sci. Expt. Sum.; p 51-59
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  • 6
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    Experiment D009: Simple navigation (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Space position-fixing techniques have been investigated by collecting data on the observable phenomena of space flight that could be used to solve the problem of autonomous navigation by the use of optical data and manual computations to calculate the position of a spacecraft. After completion of the developmental and test phases, the product of the experiment would be a manual-optical technique of orbital space navigation that could be used as a backup to onboard and ground-based spacecraft-navigation systems.
    Keywords: NAVIGATION
    Type: NASA. Manned Spacecraft Center The Gemini Program: Phys. Sci. Expt. Sum.; p 37-49
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  • 7
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    Cryogenic fuels for aircraft (1971)
    In:  CASI
    Details
    Publication Date: 2006-04-20
    Description: Application and characteristics of cryogenic fuels for air breathing gas turbine engines
    Keywords: NAVIGATION
    Type: AIRCRAFT PROPULSION 1971; P 397-420
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  • 8
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    A new guidance system figure-of-merit (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Guidance system figure of merit determining relative effectiveness of launch vehicle in delivering spacecraft onto interplanetary trajectory
    Keywords: NAVIGATION
    Type: ; 394-398. (
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  • 9
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    In-flight calibration of an interplanetary navigation instrument (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Interplanetary navigation TV camera in-flight calibration, discussing instrument error sources elimination
    Keywords: NAVIGATION
    Type: ; 394-398. (
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  • 10
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    Optimum horizontal guidance techniques for aircraft (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Optimum automatic flight control techniques in horizontal guidance of aircraft at terminal
    Keywords: NAVIGATION
    Type: ; VUE SCIENTIFIQUE ET
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  • 11
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    Star magnitude and manual navigation sighting accuracy using the Apollo T2 sextant. (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: This laboratory study investigated the effect of four star magnitudes (0, +1, +2, +3) upon the angular sighting accuracy attainable between a star and a lunar limb using a space-rated sextant with an 8-power telescope. Four males were tested. The results indicated that over a series of daily sightings sighting accuracy increases as star magnitude decreases; i.e., the angle between the actual lunar limb and the perceived lunar limb decreases as the intensity of the star increases. The significant subject and day main effects that were found indicate that each individual must be calibrated against himself and that extreme care must be taken to center the various images correctly within the sextant's field of view each time the instrument is set up. These findings are discussed in relation to further refinement of a graphic model of the distribution of energy on the retina. A discussion is also presented on the differences between sextant sighting research conducted in the laboratory and in the real, high-altitude or space environment.
    Keywords: NAVIGATION
    Type: Human Factors; 13; Oct. 197
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  • 12
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    Onboard cislunar navigation capability and procedures during Apollo lunar missions (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Apollo cislunar navigation capability and procedures, describing onboard data acquisition and digital processing equipment
    Keywords: NAVIGATION
    Type: ; ADEMIE DES SCIENCES
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  • 13
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    An examination of the effects of station longitude errors on Doppler plus range and Doppler only orbit determination solutions with an emphasis on a Viking mission trajectory (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Station longitude error effects on Doppler plus range and Doppler only orbit determination solutions, emphasizing Viking mission trajectory
    Keywords: NAVIGATION
    Type: The Deep Space Network, Vol. 4; p 71-77
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  • 14
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    Inertial navigation systems analysis. (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: This volume offers the avionic systems engineer a fundamental exposition of the mechanization and error analysis of inertial navigation systems. While the material is applicable to spacecraft and undersea navigation, emphasis is placed upon terrestrial applications on or slightly above the earth's surface. As a result, practical considerations are geared toward those aircraft navigation systems of particular current interest. Extensive use is made of perturbation techniques to develop linearized system equations, whose solutions closely approximate those obtained by nonlinear differential equations. A unified error analysis technique is developed that is applicable to virtually all system configurations. The technique provides a greatly simplified method for comparing the performance of competing system configurations.
    Keywords: NAVIGATION
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  • 15
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    Off-optimum timing of interplanetary midcourse guidance maneuvers (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Optimal timing for interplanetary midcourse guidance maneuvers for realistic cost function, indicating first and last maneuver sensitivity
    Keywords: NAVIGATION
    Type: ; 25, 26 (
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  • 16
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    ATS-5 ranging receiver and L-band experiment, volume 1 (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The ATS-5 Ranging Receiver and L-band Experiment Final Report contains information describing the L-band ranging receiver and preliminary results of test data obtained in the Mojave station. Also covered is a brief program history and description of the installation and testing phase of the program at Mojave Ground Station. The ranging receiver was designed to utilize tone ranging techniques, with the tones being supplied from the station ATS ranging system. The receiver is used in conjunction with the station L-band transmit/receive system.
    Keywords: NAVIGATION
    Type: NASA-CR-132863
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  • 17
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    An algorithm for terminal air traffic control (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An area-navigation method for automatic control of aircraft arriving in a random fashion from the en-route centers to the near terminal area is proposed. Control is exercised by a ground computer that sequences and schedules the aircraft. Altitude segregation is used to separate aircraft in velocity classes. Merging of all aircraft occurs near the outer marker. The merging region is designed so that no near misses will occur if the aircraft follow the assigned trajectories.
    Keywords: NAVIGATION
    Type: NASA-CR-128298 , ESL-P-466
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  • 18
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    Design concept (milestone 2) for space vehicle entry and landing navigation programs (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Detailed specifications and functional flow diagrams for space vehicle entry and landing navigation programs are reported. General design criteria, overall functions, and interfaces between the following three programs are considered: external observations program, noisy observations program, and navigation analysis program.
    Keywords: NAVIGATION
    Type: NASA-CR-127912 , TRW-5522.7-71-47
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  • 19
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    Dynamic testing of a single-degree-of-freedom strapdown gyroscope (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Test methods and results are presented for the equivalent average input rate of a single-degree-of-freedom gyroscope operated both open loop and with a ternary-logic pulse-torque-to-balance loop during multiaxis angular oscillation. For the open-loop tests, good agreement was obtained with theoretical results. Two-axis testing was performed for oscillations about the Input-Output axes, the Input-Spin axes, and the Spin-Output axes. These tests run in the torque-to-balance mode revealed significant departures from open-loop results in the induced drift rate. An analysis is developed explaining much of the closed-loop data presented. Test data for the gryoscope in a ternary torque-to-balance loop with constant input rates is presented. The tests demonstrate that the instrument rate linearity does not change with interrogation frequency from 3,600 to 14,400 Hz if the torque coil is tuned to offer a resistive load to the current switch. Analysis cited shows that gyroscope lag compensation eliminates multiple pulsing and other equivalent forms of degraded resolution in a wide variety of quantizing loops. This result is test verified for the ternary delta-modulator loop.
    Keywords: NAVIGATION
    Type: NASA-CR-123804 , E-2618
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  • 20
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    Study of automatic flare and decrab guidance and control system for the space shuttle (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The automatic landing of an unpowered space shuttle vehicle was studied along with the design of the guidance and flight controls, selection of the ground reference component of the landing system (signals in space), and evaluation of the performance of the overall system. The study was carried out by means of an all-digital simulation which incorporated wind shears, gusts and error models for the hardware components. The performance of the landing system operating in winds and turbulence and with hardware errors was determined by Monte Carlo techniques. It was found that the interactions of turbulence and vehicle characteristics were the limiting factors on system performance. The touchdown errors due to the measurement errors of the ground reference system were less significant. The guidance designed was predictive in the longitudinal direction and fixed path in the lateral direction.
    Keywords: NAVIGATION
    Type: NASA-CR-114436 , BAC-6272-933010
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  • 21
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    Attitude stability of spinning flexible spacecraft (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The stability of spinning flexible satellites in a force-free environment was analyzed. The satellite was modeled as a rigid core having attached to it a flexible appendage idealized as a collection of particles (point masses) interconnected by springs. Both Liapunov and Routh-Hurwitz stability procedures are used. In the former, the Hamiltonian of the system, constrained through the angular momentum integral so as to admit complete damping, is used as a testing function. Equations of motion are written using the hybrid coordinate formulation, which readily accepts a modal coordinate transformation ultimately allowing truncation to a level amenable to literal stability analysis. Closed form stability criteria are generated for the first mode of a restricted appendage model lying in a plane containing the system center of mass and orthogonal to the spin axis. The effects of spin on flexible bodies are discussed by considering a very elementary particle model. Control of passively unstable spacecraft is briefly considered.
    Keywords: NAVIGATION
    Type: NASA-CR-123669 , UCLA-ENG-7176
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  • 22
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    Broadcast control of air traffic (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The proceedings of a conference on the Omega navigation system are presented. Three significant low frequency/very low frequency possibilities are considered as follows: (1) use of Worldwide (WW) Omega, (2) use of an Omega-like system optimized for aviation in the continental United States, (3) a mix use of WW Omega and Vor, U.S. Omega and VOR, and U.S./WW Omega. It is concluded that all possibilites can be tested with current plans for WW Omega.
    Keywords: NAVIGATION
    Type: NASA-CR-125807 , QPR-2
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  • 23
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    Inertial navigation system using three TDF gyroscopic sensors not jointly mounted on a stable platform (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An inertial navigation system is described and analyzed based on two two-degree-of-freedom Schuler-gyropendulums and one two-degree-of-freedom azimuth gyro. The three sensors, each base motion isolated about its two input axes, are mounted on a common base, strapped down to the vehicle. The up and down pointing spin vectors of the two properly tuned gyropendulums track the vertical and indicate physically their velocity with respect to inertial space. The spin vector of the azimuth gyro is pointing northerly parallel to the earth axis. The system can be made self-aligning on a stationary base. If external measurements for the north direction and the vertical are available, initial disturbance torques can be measured and easily biased out. The error analysis shows that the system is practicable with today's technology.
    Keywords: NAVIGATION
    Type: NASA-CR-126358 , DLR-FB-71-94
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  • 24
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    Analysis of pilot warning indicator performance in terminal area traffic. (1971)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: Three pilot warning indicator concepts for collision hazard avoidance are analyzed using computer fast-time simulation. A hazard measure is defined based on a 1/2-g maximum horizontal acceleration, a maximum climb or dive angle of 10 deg for each aircraft, and a 20-sec warning time, through escape completion. The traffic model is based on flight tracks recorded in the Atlanta terminal area over an 11 hr period during August 1967. The basic PWI concept studied alarms on range to flashing beacons mounted on intruder aircraft as a function of relative azimuth and elevation. The alarm-hazard epoch ratio is about 17/1 to maintain the missed-alarm rate below 10%. Beacon vignetting or range-rate discrimination are shown to reduce the false-alarm rate by about 75%.
    Keywords: NAVIGATION
    Type: Journal of Aircraft; 8; Nov. 197
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  • 25
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    Feasibility study of scanning celestial Attitude System (SCADS) for Earth Resources Technology Satellite (ERTS) (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The feasibility of using the Scanning Celestial Attitude Determination System (SCADS) during Earth Resources Technology Satellite (ERTS) missions to compute an accurate spacecraft attitude by use of stellar measurements is considered. The spacecraft is local-vertical-stabilized. A heuristic discussion of the SCADS concept is first given. Two concepts are introduced: a passive system which contains no moving parts, and an active system in which the reticle is caused to rotate about the sensor's axis. A quite complete development of the equations of attitude motions is then given. These equations are used to generate the true attitude which in turn is used to compute the transit times of detectable stars and to determine the errors associated with the SCADS attitude. A more complete discussion of the analytical foundation of SCADS concept and its use for the geometries particular to this study, as well as salient design parameters for the passive and active systems are included.
    Keywords: NAVIGATION
    Type: NASA-CR-122361 , RD-1102
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  • 26
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    Dynamic errors in strapdown inertial navigation systems (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Motion-induced errors in strapdown inertial navigation systems are discussed. The errors generated in single-degree-of-freedom gyros and accelerometers are treated in great detail. These sensor errors are related to errors at the system level and common pulse rebalance techniques are compared. Since instrument single transmission characteristics are found to be important, describing function analysis is applied to nonlinear pulse torqued inertial sensor loops, and the results are compared with simulations. Two means for reducing motion-induced errors are explored: (1) selection of inertial sensor parameters, and (2) active error compensation by measuring the environment, computing the errors generated, and correcting for them.
    Keywords: NAVIGATION
    Type: NASA-CR-1962 , TR-147-3 , M213
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  • 27
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    Attitude control systems for load relief of Saturn-class launch vehicles (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effectiveness of attitude control laws that are designed to reduce bending moment loads and improve the controllability of large Saturn class boosters is discussed. These laws are referred to as load relief control systems. The two factors are assessed by simulations of varying degrees of complexity, from 2-D rigid body to 6-D with flexible body. A load relief control system, nicknamed AGE, is selected as the most effective of the various proposed schemes. This system is compared with other load relief laws and with simple attitude control. Most nominal vehicles use attitude control laws since their goal is to stay on the flight path without regard to the induced loads.
    Keywords: NAVIGATION
    Type: NASA-CR-61375
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  • 28
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    Target contrast considerations in millimeter wave radiometry for airborne navigation (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Target signal requirements for aircraft navigation systems that use radiometric receivers which map thermally emitted power radiated by terrain or power radiated by ground-based beacons are discussed. For selected millimeter wavelength bands, microwaves suffer relatively little degradation by absorption or scattering on passage through the atmosphere, despite extreme weather variations. Interest centers on 8-millimeter waves because of component availability, portability (small size), high image resolution, and all-weather capability at this wavelength. The idea of radiometric airborne navigation is introduced. Elements of radiometry, terrain radiation, and atmospheric transmission characteristics are reviewed. Data pertaining to these elements at 8 mm wavelength are collected. Calculation of radiometric contrasts is discussed for some simple models of terrain targets.
    Keywords: NAVIGATION
    Type: NASA-TM-X-62082
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  • 29
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    VHF ranging and position fixing experiment using ATS satellites: Executive summary of final report on phases 1 and 2, 25 November - 1 May 1971 (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The VHF transponders of the ATS-1 and ATS-3 geostationary satellites were used in ranging and position fixing experiments. An interrogation signal was transmitted from a ground terminal to ATS-3, which relayed it to the vehicle transponders. The vehicle that was addressed repeated the signal and its response was relayed back through both satellites to the ground terminal, where propagation times were measured; lines-of-position and fixes were computed. The 0.43 second tone-code ranging signal contained a single audio tone frequency. Ambiguity was resolved and user craft identified by a simple digital code. Seven vehicles were used in the test: three aircraft, two ships, an oceanographic buoy, and a truck. Ionospheric and multipath effects were studied. It is concluded that a VHF system could have an accuracy of + or - one nautical mile for ships and aircraft if calibration transponders are used to monitor the ionosphere.
    Keywords: NAVIGATION
    Type: NASA-CR-125537 , S-71-1109
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  • 30
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    Monte Carlo simulation of the Apollo Command Module land landing (1971)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Apollo command module land landing capability in case of abort after liftoff, describing Monte Carlo simulation procedure
    Keywords: NAVIGATION
    Type: ; 394-398. (
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  • 31
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    Guidance and navigation requirements for unmanned flyby and swingby missions to the outer planets. Volume 4: High thrust mission, part 2, phase C (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The guidance and navigation requirements for a set of impulsive thrust missions involving one or more outer planets or comets. Specific missions considered include two Jupiter entry missions of 800 and 1200 day duration, two multiple swingby missions with the sequences Jupiter-Uranus-Neptune and Jupiter-Saturn-Pluto, and two comets rendezvous missions involving the short period comets P/Tempel 2 and P/Tuttle-Giacobini-Kresak. Results show the relative utility of onboard and Earth-based DSN navigation. The effects of parametric variations in navigation accuracy, measurement rate, and miscellaneous constraints are determined. The utility of a TV type onboard navigation sensor - sighting on planetary satellites and comets - is examined. Velocity corrections required for the nominal and parametrically varied cases are tabulated.
    Keywords: NAVIGATION
    Type: NASA-CR-114398 , R-678-VOL-4-PT-2
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  • 32
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    Guidance and navigation requirements for unmanned flyby and swingby missions to the outer planets. Volume 1: Summary report (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Unmanned spacecraft missions to the outer planets are of current interest to planetary scientists, and are being studied for the post 1970 time period. Flyby, entry and orbiter missions are all being considered using both direct and planetary swingby trajectory modes. The navigation and guidance requirements for a variety of missions to the outer planets and comets including both the three and four planet Grand Tours, are summarized.
    Keywords: NAVIGATION
    Type: NASA-CR-114395 , R-678-VOL-1
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  • 33
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    Angular momentum desaturation for Skylab using gravity gradient torques (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An angular momentum desaturation method for momentum exchange devices of orbiting spacecraft is described. The specific application of the method is to the Skylab which contains three double-gimbaled control moment gyros for precise attitude control and maneuvering. It is assumed that the attitude reference is inertially fixed and that two of the vehicle principal moments of inertia are much larger than the third. Gravity gradient torques and resultant angular momentum accumulation are developed for small deviations from the reference. The assumed moment-of-inertia distribution allows desaturation about all axes with only two attitude angles each for the two axes with large moments of inertia. The necessary desaturation maneuvers can be decoupled for a special set of orbital coordinates. All maneuvers are made during the night portion of the orbit, and the percentage utilized for desaturation is selectable. Expressions for the attitude angle commands are developed assuming infinite vehicle rates. The effect of finite rates introduces an efficiency into the desaturation. Expressions for this efficiency are developed and means for compensation are treated. Arbitrary misalignments between geometric vehicle axes and principal moment-of-inertia axes are permissible. An angle bias about the sun line minimizes the angular momentum accumulation about the sun line projection into the orbital plane. Adaptive desaturation maneuver limiting consistent with the available maneuver momentum is included.
    Keywords: NAVIGATION
    Type: NASA-TM-X-64628
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    Space shuttle vehicle automatic docking study (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The material presented is divided into three main areas of accomplishment. The first is a description of the angle only docking sensor concept and the computational requirements to develop useful guidance information from the raw angle only data. The second describes the analytical effort including the MIT in-house computer simulation, the development of guidance equations and vehicle stability related thereto, and presents the results of studies covering the effects of employing Kalman filtering with the sensor. The third area presents the conclusions and recommendations resulting from the program. Much of the material has appeared in previous reports, but is included here for the sake of completeness. New material indicating how the computer might operate to identify the individual sources in the target array is included.
    Keywords: NAVIGATION
    Type: NASA-CR-115248 , E-2606
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    On optimal scheduling and air traffic control in the near terminal area (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A scheme is proposed for automated air traffic control of landing aircraft in the vicinity of the airport. Each aircraft is put under the control of an airport-based computer as soon as it enters the near-terminal area (NTA). Scheduling is done immediately thereafter. The aircraft is given a flight plan which, if followed precisely, will lead it to the runway at a prespecified time. The geometry of the airspace in the NTA is chosen so that delays are executed far from the outer marker, and violations of minimum altitude and lateral separations are avoided. Finally, a solution to the velocity mix problem is proposed.
    Keywords: NAVIGATION
    Type: NASA-CR-124640 , ESL-R-459
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    Techniques of orbital decay and long-term ephemeris prediction for satellites in earth orbit (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: In the special perturbation method, Cowell and variation-of-parameters formulations of the motion equations are implemented and numerically integrated. Variations in the orbital elements due to drag are computed using the 1970 Jacchia atmospheric density model, which includes the effects of semiannual variations, diurnal bulge, solar activity, and geomagnetic activity. In the general perturbation method, two-variable asymptotic series and automated manipulation capabilities are used to obtain analytical solutions to the variation-of-parameters equations. Solutions are obtained considering the effect of oblateness only and the combined effects of oblateness and drag. These solutions are then numerically evaluated by means of a FORTRAN program in which an updating scheme is used to maintain accurate epoch values of the elements. The atmospheric density function is approximated by a Fourier series in true anomaly, and the 1970 Jacchia model is used to periodically update the Fourier coefficients. The accuracy of both methods is demonstrated by comparing computed orbital elements to actual elements over time spans of up to 8 days for the special perturbation method and up to 356 days for the general perturbation method.
    Keywords: NAVIGATION
    Type: NASA-CR-121053
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    Techniques for generation of control and guidance signals derived from optical fields, part 2 (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The development is reported of a high resolution technique for the detection and identification of landmarks from spacecraft optical fields. By making use of nonlinear regression analysis, a method is presented whereby a sequence of synthetic images produced by a digital computer can be automatically adjusted to provide a least squares approximation to a real image. The convergence of the method is demonstrated by means of a computer simulation for both elliptical and rectangular patterns. Statistical simulation studies with elliptical and rectangular patterns show that the computational techniques developed are able to at least match human pattern recognition capabilities, even in the presence of large amounts of noise. Unlike most pattern recognition techniques, this ability is unaffected by arbitrary pattern rotation, translation, and scale change. Further development of the basic approach may eventually allow a spacecraft or robot vehicle to be provided with an ability to very accurately determine its spatial relationship to arbitrary known objects within its optical field of view.
    Keywords: NAVIGATION
    Type: NASA-CR-1798 , RF-2421
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  • 38
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    Star tracker for the Apollo telescope mount (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The star tracker for the Apollo Telescope Mount (ATM) has been designed specifically to meet the requirements of the Skylab vehicle and mission. The functions of the star tracker are presented, as well as descriptions of the optical-mechanical assembly (OMA) and the star tracker electronics (STE). Also included are the electronic and mechanical specifications, interface and operational requirements, support equipment and test requirements, and occultation information. Laboratory functional tests, environmental qualification tests, and life tests have provided a high confidence factor in the performance of the star tracker in the laboratory and on the Skylab mission.
    Keywords: NAVIGATION
    Type: NASA-TM-X-64622
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  • 39
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    The quasi-inertial and wide-deadband modes as backup attitude options for the Skylab mission (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The quasi-inertial (QI) and wide deadband (WDB) modes were investigated as alternatives to the solar inertial (SI) mode in case two control moment gyros fail during the Skylab mission. Both modes provide a substantial reduction in propellant requirements from the solar interial hold requirement with either the orbital assembly/thruster attitude control system or service module reaction control system. Spacecraft motion in the QI mode is produced by a command rate and results in a small amplitude oscillation (17 deg, maximum) about the SI orientation. In the WDB mode a somewhat similar, but larger amplitude motion (35 deg maximum) about the SI orientation is developed by appropriate choice of controller deadbands and switch line slopes.
    Keywords: NAVIGATION
    Type: NASA-CR-123266 , TM-71-1022-3 , BA-145A
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  • 40
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    Aircraft altitude determination using multipath information in an angle-measuring navigation satellite system (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: In an angle-measuring navigation satellite system using a pair of crossed interferometers located on a satellite in synchronous orbit, three parameters are needed to determine a user's position unambiguously. These are the phase differences between received signals which were transmitted by the two antennas on each of the two interferometers, and the user's altitude. The two phase difference measurements yield a line of possible user locations, and the addition of the altitude measurement reduces this line to a single point. A method is proposed which makes use of the navigation signals received after reflection off the earth's surface. The iterative procedure employs the arrival time difference between direct and reflected signals. Based on previous calculations of errors in measuring the electrical parameters it is concluded that, for North Atlantic coverage and specular reflection, altitude measurements can be made with a 1-sigma error of 65 meters.
    Keywords: NAVIGATION
    Type: NASA-CR-124625 , REPT-72-12
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  • 41
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    Manned Mars lander launch-to-rendezvous analysis for a 1981 Venus-swingby mission (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A description is given of the return of a manned Mars lander by a launch from the surface of Mars to some intermediate orbit, with subsequent maneuvers to rendezvous with a primary spacecraft (called the orbiter) in a Mars parking orbit. The type of Mars mission used to demonstrate the analytical technique includes a Venus swingby on the Mars-to-Earth portion of the trajectory in order to reduce the total mission velocity requirement. The total velocity requirement for the mission considered (if inplane launches are assumed) is approximately 17,500 ft/sec.
    Keywords: NAVIGATION
    Type: NASA-TN-D-6555 , MSC-S-282
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  • 42
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    Sun compass error model (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An error model is described for the Apollo 15 sun compass, a contingency navigational device. Field test data are presented along with significant results of the test. The errors reported include a random error resulting from tilt in leveling the sun compass, a random error because of observer sighting inaccuracies, a bias error because of mean tilt in compass leveling, a bias error in the sun compass itself, and a bias error because the device is leveled to the local terrain slope.
    Keywords: NAVIGATION
    Type: NASA-TM-X-67446 , MSC-04445 , MSC-IN-71-FM-241
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    A method for star vector determination from alignment optical telescope sighting (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A method is described for determining the measured star vector in LM body coordinates when the measurement data consist of a spiral measurement, a cusor measurement, and a time associated with each measurement. The method is defined from alignment optical telescope (AOT) sightings from the LM on the lunar surface. This formulation will be coded into the real-time computer complex off-line AOT and gravity (AOT+G) bench program, the Gravity-Optics LM Attitude and Position (GOLAP) program.
    Keywords: NAVIGATION
    Type: NASA-TM-X-67470 , MSC-IN-71-FM-242 , MSC-04446
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    Lunar surface navigation analysis (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The accuracy of the crew position obtained by using a line-of-sight device such as a sun compass or the rover television camera and the prominent mountains such as Hadley and Hadley delta was investigated. It was determined that with errors of 1 deg (noise only), the crew position can be obtained to sigma sub phi = 850 feet and sigma sub lambda = 400 feet using Hadley and Hadley delta. The addition of West Mountain reduced the errors to 600 and 400 feet, respectively.
    Keywords: NAVIGATION
    Type: NASA-TM-X-67443 , MSC-04241 , MSC-IN-71-FM-155
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  • 45
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    A guide to onboard checkout. Volume 1: Guidance, navigation and control (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results are presented of a study of onboard checkout techniques, as they relate to space station subsystems, as a guide to those who may need to implement onboard checkout in similar subsystems. Guidance, navigation, and control subsystems, and their reliability and failure analyses are presented. Software and testing procedures are also given.
    Keywords: NAVIGATION
    Type: NASA-CR-115261 , IBM-71W-00308-VOL-1
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  • 46
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    Broadcast control of air traffic (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Concepts of increased pilot participation in air traffic control are presented. The design of an air traffic control system for pilot usage is considered. The operating and safety benefits of LF/VLF approaches in comparison to current nonprecision approach procedures and systems are discussed. With a good national system plan, flight testing and validation, and the use of local differential, or general diurnal, corrections, the LF/VLF system would provide service superior to that presently available.
    Keywords: NAVIGATION
    Type: NASA-CR-124696 , QPR-1
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  • 47
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    The Mariner Mars 1971 gimbal actuator (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The actuator that will point the gimbaled engine, thus performing the autopilot actuation function for the Mariner Mars 1971 spacecraft, is described. The gimbaled engine has two axes of freedom, providing two-axis control to the spacecraft. Motion for the two axes is provided by identical and interchangeable actuators-gearless electromechanical linear servomechanisms. Each actuator is designed to have a long service life in the space environment and to be able to function at speeds ranging from hours per cycle to cycles per second.
    Keywords: NAVIGATION
    Type: NASA. Goddard Space Flight Center 5th Aerospace Mech. Symp.; p 185-191
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  • 48
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    Attitude control of an orbiting space vehicle. (1971)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Study of the normal and clamped modes of operation and dynamic response characteristics of the gimbaled control moment gyro (CMG) designed to fulfill the stringent pointing requirements of the Skylab telescope mount when the spacecraft is under the influence of both external and internal torques. The results indicate that the clamped mode of operation provides a feasible approach for significantly improving the system characteristics.
    Keywords: NAVIGATION
    Type: Journal of Spacecraft and Rockets; 8; Nov. 197
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  • 49
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    Guidance and control of flight vehicles (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Progress reports on guidance and attitude control mechanisms of different flight vehicles are presented. The vehicles considered include orbiting spacecraft, supersonic aircraft, and general aviation aircraft. Data also cover orbital transfer using low thrust, automatic landing logic for aircraft, optimal and three dimensional turns for supersonic aircraft, and orbital rendezvous.
    Keywords: NAVIGATION
    Type: NASA-CR-127268
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  • 50
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    Fixed-angle translunar guidance procedures using onboard optical measurements (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Fixed angle translunar guidance procedures using onboard optical measurements
    Keywords: NAVIGATION
    Type: NASA-TN-D-6461 , L-7811
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  • 51
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    Attitude stability of dissipative dual-spin spacecrafts (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Spin-axis attitude stability of dissipative dual spin spacecrafts in force-free environment
    Keywords: NAVIGATION
    Type: NASA-TM-X-65681 , X-730-71-326
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  • 52
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    Joint determination of orbits of spacecraft and moons of Mars by optical sighting of the moons (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Scanning optical system to provide attitude and trajectory of unmanned spacecraft during orbit about Mars
    Keywords: NAVIGATION
    Type: NASA-CR-1805 , RD-2013
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  • 53
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    On the attitude stability of the SAS A spacecraft (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Effects of energy dissipation on systems stability of SAS A spacecraft
    Keywords: NAVIGATION
    Type: NASA-TM-X-65557 , X-732-71-187
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  • 54
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    ATS ranging and position fixing experiments Progress report, 1 Nov. 1970 - 31 Jan. 1971 (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: ATS ranging and position fixing experiments with 4-day synoptic ionosphere propagation and 24-hour synoptic measurements
    Keywords: NAVIGATION
    Type: NASA-CR-118648 , S-71-1024
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  • 55
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    IMP-1-D-4.5.5 - Description and summary of qualification testing of the IMP-1 attitude control system and Yo-Yo despin system (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Results and description of qualification tests of attitude control system and yo-yo despin system in flight configuration as installed on IMP-1 spacecraft
    Keywords: NAVIGATION
    Type: NASA-TM-X-65473 , X-722-71-30
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  • 56
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    A technique for evaluating parameter variations for automatically controlled aircraft with an application to the landing approach (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Minimizing performance criterion to analyze ability of automatically controlled aircraft to maintain accurate flight path control during landing approach
    Keywords: NAVIGATION
    Type: NASA-TN-D-6230 , A-3244
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  • 57
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    Preliminary determination of spacecraft trajectories using on-board optical measurements (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Star selection and bias error eliminating calibrations for five onboard optical measurements used to determine spacecraft trajectories
    Keywords: NAVIGATION
    Type: NASA-TN-D-6551 , A-3522
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  • 58
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    Kalman filter initialization using prior information applied to Apollo midcourse navigation (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Kalman filtering techniques for estimating position and velocity of spacecraft
    Keywords: NAVIGATION
    Type: NASA-CR-116153 , T-553
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  • 59
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    Analysis of a navigation concept employing a spinning radiating interferometer in geostationary orbit (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Analysis of concept of spin-stabilized synchronous satellite carrying interferometer transmitting CW signals in L-band
    Keywords: NAVIGATION
    Type: NASA-CR-121756 , REPT-72-05
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  • 60
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    Project/Space Shuttle - Space shuttle guidance, navigation and control design equations, volume 1 (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Introductory information for equations to perform guidance, navigation, and control onboard computation functions for space shuttle orbiter
    Keywords: NAVIGATION
    Type: NASA-TM-X-67218 , MSC-04217-VOL-1
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  • 61
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    Control moment gyro for Skylab (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Skylab control moment gyroscope inner gimbal design and thermal vacuum and environmental tests
    Keywords: NAVIGATION
    Type: NASA-TM-X-64583
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  • 62
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    Midcourse and approach guidance requirements for simplified onboard control of moon to earth trajectories (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Development of procedures for midcourse and approach guidance of moon to earth trajectories based on optical angular measurements and onboard calculations
    Keywords: NAVIGATION
    Type: NASA-TN-D-6343 , L-7662
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  • 63
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    Geodetic satellite results for Deep Space Station coordinates (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Optical tracking data from geodetic satellites for deep space station coordinates
    Keywords: NAVIGATION
    Type: NASA-TM-X-65550 , X-552-71-109
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  • 64
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    Vehicle attitude - An analysis of flight 4.272 UA (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Postflight analysis of Aerobee rocket vehicle attitude determination with solar aspect sensors and magnetometers
    Keywords: NAVIGATION
    Type: NASA-TM-X-65570 , X-743-71-103
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  • 65
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    Skylab attitude and pointing control system (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Development and characteristics of attitude and pointing control system for Skylab space station
    Keywords: NAVIGATION
    Type: NASA-TN-D-6068 , M-211
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  • 66
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    Nutational stability of a dual-spin satellite under the influence of applied reaction torques (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: It is assumed that since the solar paddle attachments to the hub of the spacecraft are not rigidly locked, the effect of the solar panels can be replaced by a constant reaction torque acting on the hub of the spacecraft. This could result in the satellite having an equilibrium motion about an axis displaced from the nominal axis of symmetry. The variational equations of motion are developed about such an equilibrium position using the SAS-A spacecraft as a model. Energy dissipation on the rotor as well as the main body is included. This nonautonomous set of differential equations are linearized and transformed to an autonomous set using the Liapunov reducibility theorem. The stability of the kinematically similar system is examined numerically using representative SAS-A parameters for the case when either pair of solar panels is assumed to be loosely attached. Stability is verified for small system nutation angles (0.1 degree).
    Keywords: NAVIGATION
    Type: NASA-TM-X-65789 , X-732-71-335
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  • 67
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    Investigation of techniques for improving Saturn 5 RF tracking and ranging systems (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Results of theoretical analyses of 12 problems are presented and comparisons of theoretical and experimental results are given. The investigations covered were: (1) techniques for improving the Saturn radar altimeter, (2) performance of the phase lock loop of the offset Doppler transponder, (3) signal processing equipment design for an orbital altitude radar return experiment, (4) spectral studies of signals present in the command and communication system (CCS) up-link transmitter, (5) intermodulation in the CCS down-link data demodulators, (6) error rate performance of the CCS transponder command demodulator, (7) flame attenuation effects on telemetry transmissions during Saturn launches, (8) design of a digital television system which converts a standard monochrome picture to a slow-scan picture, (9) methods of obtaining an additional CCS 72-kilobit/sec telemetry channel, (10) computation of the CCS S-band down-link spectra, (11) modeling of portions of the communications systems, and (12) modeling of a telemetry transmitter.
    Keywords: NAVIGATION
    Type: NASA-CR-121074
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  • 68
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    A method for lunar roving vehicle position determination from three landmark observations with a sun compass (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A simplified method is described for determining the position of the lunar roving vehicle on the lunar surface during Apollo 15. The method is based upon sun compass azimuth measurements of three lunar landmarks. The difference between the landmark azimuth and the sun azimuth is measured and the resulting data are voice relayed to the Mission Control Center for processing.
    Keywords: NAVIGATION
    Type: NASA-TM-X-67447 , MSC-04440 , MSC-IN-71-FM-238
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  • 69
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    The attitude determination of a three axes stabilized spacecraft (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An approach is presented for attitude determination of a three axis stabilized spacecraft. The employment of two independent vectors is described whose components with respect to two reference coordinate axes can be known. Such two coordinate axes are right-handed three mutually orthogonal axes systems of which one is fixed in the spacecraft and the other has known orientation in space. The relationship between the two systems are then expressed as mathematical equations with the use of the two reference vectors. By computing the derived equations, the attitude of the spacecraft can be obtained.
    Keywords: NAVIGATION
    Type: NASA-TM-X-65744 , X-565-71-430
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    VHF Ranging and Position Fixing Experiment Using ATS Satellites: Final Report on Phases 1 and 2, 25 November 1968 - 1 May 1971 (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The testing program with the ATS-1 and ATS-3 spacecraft showed that geostationary satellites can provide superior communications and position surveillance for mobile craft. Inexpensive modifications to conventional mobile communications equipment aboard the craft can provide reliable, high quality voice and digital communications with distant ground stations and other vehicles, and automatic surveillance of the positions of all the craft by a ground facility. The tests also demonstrated the location and automatic readout of remote data collection platforms. Frequency modulation signals with the narrow audio and radio frequency bandwidths of terrestrial mobile radio communications were relayed through the VHF transponders of the geostationary satellites. The voice and digital communications were far superior in reliability and quality to long-distance mobile communications by other means. It was shown that one satellite can provide nearly uniform high quality performance over approximately one-third of the earth's surface. Position fixes by range measurement from the two satellites were accurate to approximately one nautical mile, except near the equator and the poles.
    Keywords: NAVIGATION
    Type: NASA-CR-125538 , S-71-1109
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    ATS-1/ATS-3 dual satellite navigation study (1971)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A study which illustrated the feasibility of implementing an on-board aircraft navigation system based on using the ATS-1 and ATS-3 satellites, the modified Omega Position Location Equipment (OPLE) Control Center, and a suitable aircraft terminal was conducted. The report provides: (1) a consideration of the problems of satellite navigation and an objective definition of the optimum system under the constraints of its specified components, (2) a description of the necessary modifications to the OPLE Control Center, the design of an aircraft terminal, and the design of ground reference terminals, and (3) an outline of an experiment plan and an estimate of the cost to be expected in conducting the program.
    Keywords: NAVIGATION
    Type: NASA-CR-130213 , TI-U1-835300-F
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  • 72
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    Multipath/RFI/modulation study for DRSS-RFI problem: Voice coding and intelligibility testing for a satellite-based air traffic control system (1971)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Analog and digital voice coding techniques for application to an L-band satellite-basedair traffic control (ATC) system for over ocean deployment are examined. In addition to performance, the techniques are compared on the basis of cost, size, weight, power consumption, availability, reliability, and multiplexing features. Candidate systems are chosen on the bases of minimum required RF bandwidth and received carrier-to-noise density ratios. A detailed survey of automated and nonautomated intelligibility testing methods and devices is presented and comparisons given. Subjective evaluation of speech system by preference tests is considered. Conclusion and recommendations are developed regarding the selection of the voice system. Likewise, conclusions and recommendations are developed for the appropriate use of intelligibility tests, speech quality measurements, and preference tests with the framework of the proposed ATC system.
    Keywords: NAVIGATION
    Type: NASA-CR-122434 , ASAO-PR20020-2
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  • 73
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    A comparison and evaluation of satellite derived positions of tracking stations (1971)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A comparison is presented of sets of satellite tracking station coordinate values published in the past few years by a number of investigators, i.e. Goddard Space Flight Center, Smithsonian Astrophysical Observatory, Ohio State University, The Naval Weapons Laboratory, Air Force Cambridge Research Laboratories, and Wallops Island. The comparisons have been made in terms of latitude, longitude and height. The results of the various solutions have been compared directly and also with external standards such as local survey data and gravimetrically derived geoid heights. After taking into account systematic rotations, latitude and longitude agreement on a global basis is generally 15 meters or better, on the North American Datum agreement is generally better than 10 meters. Allowing for scale differences (of the order of 2 ppm) radial agreement is generally of the order of 10 meters.
    Keywords: NAVIGATION
    Type: NASA-TM-X-65814 , X-553-71-257 , Fall Meeting of the Am. Geophys. Union; Dec 01, 1970
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  • 74
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    Study of automatic and manual terminal guidance and control systems for space shuttle vehicles (1971)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A summary of the aerodynamic characteristics of the delta orbiter space shuttle vehicle is presented. Selected guidance and control system parameters, flight path geometry, landing performance obtained with winds and turbulence, and the influence of vehicle L/D on that performance are included.
    Keywords: NAVIGATION
    Type: NASA-CR-114407 , REPT-71-0225-00-01
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  • 75
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    CR-100 implementation study for space shuttle (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Examining performance of CR-100 CRIS equipment for space shuttle use
    Keywords: NAVIGATION
    Type: NASA-CR-115147 , FTR/16-1
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  • 76
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    Optimal lateral guidance for low L/D shuttle vehicle entry (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Technique for designing switching thresholds in lateral guidance of entry vehicle
    Keywords: NAVIGATION
    Type: NASA-CR-115146 , E-2592
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  • 77
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    Irradiation effects on manual sighting accuracy of a space flight rated sextant using simulated lunar and stellar targets (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Lunar disk luminance effects on manual sighting accuracy of space sextant using simulated lunar and stellar targets
    Keywords: NAVIGATION
    Type: NASA-TN-D-6507 , A-3883
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  • 78
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    Project/Space Shuttle - Space shuttle guidance, navigation and control design equations. Volume 3 - Orbital operations (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Initial data for space shuttle orbiter guidance, navigation, and control equations for orbital operations of flight, rendezvous, docking, and stationkeeping
    Keywords: NAVIGATION
    Type: NASA-TM-X-67215 , MSC-04217-VOL-3
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  • 79
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    MESS /Misalignment Estimation Software System/ for in-flight alignment and calibration of spacecraft attitude sensors (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Misalignment estimation software system for calibrating in-flight slew angle scale factors and drift rates of OAO gyros
    Keywords: NAVIGATION
    Type: NASA-TM-X-65667 , AAS-71-357 , X-514-71-323
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  • 80
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    Project/Space Shuttle - Space shuttle guidance, navigation and control design equations. Volume 2 - Preflight through orbit insertion (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Initial data for space shuttle orbiter guidance, navigation, and control equations for preflight, boost, separation, orbit insertion, and ascent abort phases
    Keywords: NAVIGATION
    Type: NASA-TM-X-67217 , MSC-04217-VOL-2
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  • 81
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    Gravity gradient attitude control system Patent (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Gravity gradient attitude control system with gravity gradiometer and reaction wheels for artificial satellite attitude control
    Keywords: NAVIGATION
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  • 82
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    Single axis reference strapdown inertial measuring unit (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Design and tests of single-axis reference strapdown inertial measuring unit
    Keywords: NAVIGATION
    Type: NASA-TM-X-64586
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  • 83
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    Mascot - A new concept in guidance (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Trajectory algorithm for complete trajectory from liftoff to landing with optimal control and onboard flight computer for use in manned space shuttle
    Keywords: NAVIGATION
    Type: NASA-TM-X-64573
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  • 84
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    Equilibrium states for a class of dual spin spacecraft (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Equilibrium states and attitude stability of dual spin spacecraft
    Keywords: NAVIGATION
    Type: NASA-TR-R-362 , G-1011
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  • 85
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    A statistical study of ability of simulated pilots to control the approach and descent of the lunar module to the lunar surface (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Statistical analysis of simulated pilot ability to control lunar module approach and descent to lunar surface
    Keywords: NAVIGATION
    Type: NASA-TN-D-6113 , L-7377
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  • 86
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    Field tests using dead reckoning and monoptic video for remote lunar surface navigation (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Field tests of simulated remote navigation control system for lunar surface vehicle
    Keywords: NAVIGATION
    Type: NASA-TM-X-64567
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  • 87
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    General test plan redundant sensor strapdown IMU evaluation program (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The general test plan for a redundant sensor strapdown inertial measuring unit evaluation program is presented. The inertial unit contains six gyros and three orthogonal accelerometers. The software incorporates failure detection and correction logic and a land vehicle navigation program. The principal objective of the test is a demonstration of the practicability, reliability, and performance of the inertial measuring unit with failure detection and correction in operational environments.
    Keywords: NAVIGATION
    Type: NASA-CR-130722 , TRW-18313-6002-R0-00
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  • 88
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    Detailed Test Plan Redundant Sensor Strapdown IMU Evaluation Program (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The test plan for a redundant sensor strapdown inertial measuring unit evaluation program is presented. The subjects discussed are: (1) test philosophy and limitations, (2) test sequence, (3) equipment specifications, (4) general operating procedures, (5) calibration procedures, (6) alignment test phase, and (7) navigation test phase. The data and analysis requirements are analyzed.
    Keywords: NAVIGATION
    Type: NASA-CR-123513 , TRW-18313-6003-R0-00
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  • 89
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    Study of precise positioning at L-band using communications satellites (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The L-band positioning experiment is reported which encompassed experiment design, experimentation, and data reduction and analysis. In the experiment the ATS-5 synchronous satellite L-band transponder was used in conjunction with the modified ALPHA 2 navigation receivers to demonstrate the technical capability of precision position fixing for oceanographic purposes. The feasibility of using relative ranging techniques implemented by two identical receiving systems, properly calibrated, to determine a line of position accurately on the surface of the earth was shown. The program demonstrated the level of resolution, repeatibility, precision, and accuracy of existing modest-cost effective navigation equipment. The experiment configuration and data reduction techniques were developed in parallel with the hardware modification tasks. Test results verify the ability of a satellite-based system to satisfy the requirements of precision position fixing.
    Keywords: NAVIGATION
    Type: NASA-CR-62095
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  • 90
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    Guidance system operations plan for manned cm earth orbital and lunar missions using program Colossus 3. Section 2: Data links (1971)
    In:  CASI
    Details
    Publication Date: 2019-07-20
    Description: The data links for use with the guidance system operations plan for manned command module earth orbital and lunar missions using program Colossus 3 are presented. The subjects discussed are: (1) digital uplink to CMC, (2) command module contiguous block update, (3) CMC retrofire external data update, (4) CMC digital downlink, and (5) CMC entry update.
    Keywords: NAVIGATION
    Type: NASA-CR-115747 , R-577-SECT-2-REV-15
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  • 91
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    Space shuttle landing navigation using precision distance measuring equipment (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Evaluation of precision distance measuring equipment for space shuttle landing navigation
    Keywords: NAVIGATION
    Type: NASA-CR-115138
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  • 92
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    PPCS engineering model design (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Engineering model design of equipment comprising precision pointing control system
    Keywords: NAVIGATION
    Type: NASA-CR-121912 , TRW-13900-6011-R0-01
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  • 93
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    Mathematical concept and historical development of the mascot guidance technique for space vehicles (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Manned shuttle comprehensive optimization and targeting program (MASCOT)
    Keywords: NAVIGATION
    Type: NASA-TM-X-64608
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  • 94
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    A unified formalism for position determination from various navigation measurements (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Development of technique for coordinate determination of moving vehicles and unified description for extracting position information from combinations of measurements
    Keywords: NAVIGATION
    Type: NASA-TN-D-6417 , A-3875
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  • 95
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    Operational considerations for the use of loran-C skywaves for time synchronization (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Time synchronization of loran C navigation system and characteristics of sky wave reception operation
    Keywords: NAVIGATION
    Type: NASA-TM-X-65515 , X-573-71-148
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  • 96
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    Orbit selection considerations for earth resources observations (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Orbital mechanics and observation tradeoffs for earth resources satellite
    Keywords: NAVIGATION
    Type: NASA-TM-X-2156
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  • 97
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    Navigation training for current space flights (1971)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Apollo simulator navigation and docking training techniques, discussing manned LM and CSM key role performance
    Keywords: NAVIGATION
    Type: ; VUE SCIENTIFIQUE ET|MEETING ON NAVIGATION TRAINING FOR CURRENT SPACE FLIGHTS; Jul 01, 1970 - Jul 02, 1970; COLORADO SPRINGS, CO
    Format: text
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  • 98
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    A computerized landmark navigator (1971)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Computer program for determining roving vehicle position and heading on lunar surface by landmarks
    Keywords: NAVIGATION
    Type: HAWAII INTERNATIONAL CONFERENCE ON SYSTEM SCIENCES; Jan 12, 1971 - Jan 14, 1971; HONOLULU, HI
    Format: text
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  • 99
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    VHF navigation experiment (1971)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Navigational accuracy resulting from sidetone signals relayed by two synchronous ATS-1 and ATS-3 satellites and application to aircraft navigation
    Keywords: NAVIGATION
    Type: NASA-CR-121977 , U9-832400-F
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  • 100
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    ATS ranging and position fixing experiments (1971)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Tone code range and position system adapted to L band frequency of ATS 5
    Keywords: NAVIGATION
    Type: NASA-CR-121622
    Format: application/pdf
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