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  • NAVIGATION
  • 1990-1994
  • 1970-1974  (659)
  • 1960-1964  (387)
  • 1930-1934
  • 1
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    Landing rates for mixed STOL and CTOL traffic (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A study was made to determine the expected landing rate for STOL-only traffic and mixed STOL-CTOL traffic. The conditions used vary from present day standards to an optimistic estimate of possible 1985 conditions. A computer program was used to determine the maximum landing rate for the specified conditions and aircraft mix. The results show that the addition of STOL on a CTOL runway increases the total landing rate if the STOL airborne spacing can be reduced by use of improved navigation equipment. Further, if both takeoff and landings are performed on the same runway, the addition of STOL traffic will allow an increase in the total operation rate, even with existing spacing requirements.
    Keywords: NAVIGATION
    Type: NASA-TN-D-7666 , A-5044
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Investigation of application of two-degree-of-freedom dry tuned-gimbal gyroscopes to strapdown navigation systems (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The work is described which was accomplished during the investigation of the application of dry-tuned gimbal gyroscopes to strapdown navigation systems. A conventional strapdown configuration, employing analog electronics in conjunction with digital attitude and navigation computation, was examined using various levels of redundancy and both orthogonal and nonorthogonal sensor orientations. It is concluded that the cost and reliability performance constraints which had been established could not be met simultaneously with such a system. This conclusion led to the examination of an alternative system configuration which utilizes an essentially new strapdown system concept. This system employs all-digital signal processing in conjunction with the newly-developed large scale integration (LSI) electronic packaging techniques and a new two-degree-of-freedom dry tuned-gimbal instrument which is capable of providing both angular rate and acceleration information. Such a system is capable of exceeding the established performance goals.
    Keywords: NAVIGATION
    Type: NASA-CR-132419
    Format: application/pdf
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  • 3
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    Apollo lunar descent guidance (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Apollo lunar-descent guidance transfers the Lunar Module from a near-circular orbit to touchdown, traversing a 17 deg central angle and a 15 km altitude in 11 min. A group of interactive programs in an onboard computer guide the descent, controlling altitude and the descent propulsion system throttle. A ground-based program pre-computes guidance targets. The concepts involved in this guidance are described. Explicit and implicit guidance are discussed, guidance equations are derived, and the earlier Apollo explicit equation is shown to be an inferior special case of the later implicit equation. Interactive guidance, by which the two-man crew selects a landing site in favorable terrain and directs the trajectory there, is discussed. Interactive terminal-descent guidance enables the crew to control the essentially vertical descent rate in order to land in minimum time with safe contact speed. The altitude maneuver routine uses concepts that make gimbal lock inherently impossible.
    Keywords: NAVIGATION
    Type: Automatica; 10; Mar. 197
    Format: text
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  • 4
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    Ambiguity resolution in systems using Omega for position location (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The lane ambiguity problem prevents the utilization of the Omega system for many applications such as locating buoys and balloons. The method of multiple lines of position introduced herein uses signals from four or more Omega stations for ambiguity resolution. The coordinates of the candidate points are determined first through the use of the Newton iterative procedure. Subsequently, a likelihood function is generated for each point, and the ambiguity is resolved by selecting the most likely point. The method was tested through simulation.
    Keywords: NAVIGATION
    Type: IEEE Transactions on Communications; COM-22; Mar. 197
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  • 5
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    Description of the attitude control, guidance and navigation space replaceable units for automated space servicing of selected NASA missions (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Control elements such as sensors, momentum exchange devices, and thrusters are described which can be used to define space replaceable units (SRU), in accordance with attitude control, guidance, and navigation performance requirements selected for NASA space serviceable mission spacecraft. A number of SRU's are developed, and their reliability block diagrams are presented. An SRU assignment is given in order to define a set of feasible space serviceable spacecraft for the missions of interest.
    Keywords: NAVIGATION
    Type: NASA-CR-139589 , ATR-74(7341)-1
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  • 6
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    Landing approach evaluation of an integrated CRT display for general aviation aircraft (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A flight director adaptable to general aviation aircraft was evaluated for the landing approach task in a twin turbojet business aircraft. The flight director combined aircraft heading, pitch and roll atitude, and ILS (Instrument Landing System) signals into a single picture on a small cathode ray tube (CRT) to give the pilot an integrated picture of the aircraft situation. The display is unique in that it presents the information on a CRT and gives quasi-command signals to the pilot. The particular display investigated was a preproduction version of the Kaiser Model FP-50 flight director. Approaches made with visual references only, with a conventional ILS displacement instrument, and with the CRT display were compared in terms of tracking performance and pilot workload. Tracking performance of three research pilots using the CRT display was superior to that using the conventional ILS instrument and comparable to that under VFR conditions. Pilot workload (based on pilot comments) was not clearly decreased.
    Keywords: NAVIGATION
    Type: NASA-TM-X-3096 , A-5208
    Format: application/pdf
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  • 7
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    A STOL terminal area navigation system (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The mechanization and performance of a STOL terminal area navigation system are described. The purpose of the navigation system is to allow flying with precision 4D-guidance along complex flight paths in the terminal area, and to develop requirements for STOL operations in the 1980s. The navigation aids include an experimental microwave landing system, MODILS. The systems description begins with the navigation aids. It is shown how the data are transformed and combined with other data to obtain position and velocity estimates. Also presented are some of the design changes and other features that were introduced as a result of flight testing. The various ways of displaying navigation-derived data are given. Finally, simulator and flight test results are discussed.
    Keywords: NAVIGATION
    Type: NASA-TM-X-62348
    Format: application/pdf
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  • 8
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    Navigation and guidance requirements for commercial VTOL operations (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The NASA Langley Research Center (LaRC) has undertaken a research program to develop the navigation, guidance, control, and flight management technology base needed by Government and industry in establishing systems design concepts and operating procedures for VTOL short-haul transportation systems in the 1980s time period. The VALT (VTOL Automatic Landing Technology) Program encompasses the investigation of operating systems and piloting techniques associated with VTOL operations under all-weather conditions from downtown vertiports; the definition of terminal air traffic and airspace requirements; and the development of avionics including navigation, guidance, controls, and displays for automated takeoff, cruise, and landing operations. The program includes requirements analyses, design studies, systems development, ground simulation, and flight validation efforts.
    Keywords: NAVIGATION
    Type: NASA-CR-132423 , ASI-TR-74-17
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  • 9
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    Study of effects of uncertainties of comet and asteroid encounter and contact guidance requirements. Part 2: Tumbling problem studies (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The problem of determining the rotational motion of a tumbling celestial body of the asteroid type using spacecraft-acquired data is addressed. The rotational motion of the body is modeled by free-Eulerian motion of a triaxial, rigid body and its translational motion with respect, to a nonrotating, observing spacecraft, which is not thrusting, is assumed to be uniform during the time observations are made. The mathematical details which form the basis for a digital simulation of the motion and observations are presented. Two algorithms for determining the motion from observations for the special case of uniform rotational motion are given.
    Keywords: NAVIGATION
    Type: NASA-CR-120330
    Format: application/pdf
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  • 10
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    Flight investigation of manual and automatic VTOL decelerating instrument approaches and landings (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A flight investigation was undertaken to study the problems associated with manual and automatic control of steep, decelerating instrument approaches and landings under simulated instrument conditions. The study was conducted with a research helicopter equipped with a three-cue flight-director indicator. The scope of the investigation included variations in the flight-director control laws, glide-path angle, deceleration profile, and control response characteristics. Investigation of the automatic-control problem resulted in the first automated approach and landing to a predetermined spot ever accomplished with a helicopter. Although well-controlled approaches and landings could be performed manually with the flight-director concept, pilot comments indicated the need for a better display which would more effectively integrate command and situation information.
    Keywords: NAVIGATION
    Type: NASA-TN-D-7524 , L-9311
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  • 11
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    Discrete optimal control approach to a four-dimensional guidance problem near terminal areas (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Description of a computer-oriented technique to generate the necessary control inputs to guide an aircraft in a given time from a given initial state to a prescribed final state subject to the constraints on airspeed, acceleration, and pitch and bank angles of the aircraft. A discrete-time mathematical model requiring five state variables and three control variables is obtained, assuming steady wind and zero sideslip. The guidance problem is posed as a discrete nonlinear optimal control problem with a cost functional of Bolza form. A solution technique for the control problem is investigated, and numerical examples are presented. It is believed that this approach should prove to be useful in automated air traffic control schemes near large terminal areas.
    Keywords: NAVIGATION
    Type: International Journal of Control; 20; Aug. 197
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  • 12
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    Interplanetary navigation using pulsating radio sources (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Radio beacons with distinguishing signatures exist in nature as pulsating radio sources (pulsars). These objects radiate well determined pulse trains over hundreds of megahertz of bandwidth at radio frequencies. Since they are at known positions, they can also be used as navigation beacons in interplanetary space. Pulsar signals are weak and dispersive when viewed from earth. If an omnidirectional antenna is connected to a wideband receiver (200 MHz bandwidth centered at 200 MHz) in which dispersion effects are removed, nominal spacecraft position errors of 1500 km can be obtained after 24 h of signal integration. An antenna gain of 10 db would produce errors as low as 150 km. Since the spacecraft position is determined from the measurement of the phase of a periodic signal, ambiguities occur in the position measurement. Simultaneous use of current spacecraft navigation schemes eliminates these ambiguities.
    Keywords: NAVIGATION
    Type: NASA-CR-140398 , JPL-TR-32-1594
    Format: application/pdf
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  • 13
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    Mariner IX optical navigation using Mars lit limb (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Optical spacecraft navigation data, i.e., the lit limb TV image of Mars, acquired during the approach phase of the Mariner IX spacecraft to Mars, has been successfully demonstrated to augment the radio spacecraft tracking data. Accurate in-flight calibration of the TV instrument and the scan platform was performed by referencing stars and planets. Simulated real-time processing and the detailed postflight analyses of the onboard optical data have shown that planet limb data is an important data source in a far-encounter period for which other types of onboard optical measurements, e.g., natural satellite(s) of the target planet with star background, may not be available.
    Keywords: NAVIGATION
    Type: AIAA PAPER 73-251
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  • 14
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    A flight investigation of a terminal area navigation and guidance concept for STOL aircraft (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A digital avionics system referred to as STOLAND has been test-flown in the NASA CV-340 to obtain performance data for time-controlled guidance in the manual flight director mode. The advanced system components installed in the cockpit included an electronic attitude director indicator and an electronic multifunction display. Navigation guidance and control computations were all performed in the digital computer. Approach paths were flown which included a narrow 180-deg turn and a 1-min, 5-deg straight-in approach to the 30-m altitude go-around point. Results are presented for 20 approaches: (1) blended radio/inertial navigation using TACAN and a microwave scanning beam landing guidance system (MODILS) permitted a smooth transition from area navigation (TACAN) to precision terminal navigation (MODILS), (2) guidance system (flight director) performance measured at an altitude of 30.5 m was within that prescribed for category II CTOL operations on a standard runway, and (3) time of arrival at a point about 2 mi from touchdown was about 4 sec plus or minus sec later than the computed nominal arrival time.
    Keywords: NAVIGATION
    Type: NASA-TM-X-62375
    Format: application/pdf
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  • 15
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    Mariner Mars 1971 optical navigation demonstration (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The feasibility of using a combination of spacecraft-based optical data and earth-based Doppler data to perform near-real-time approach navigation was demonstrated by the Mariner Mars 71 Project. The important findings, conclusions, and recommendations are documented. A summary along with publications and papers giving additional details on the objectives of the demonstration are provided. Instrument calibration and performance as well as navigation and science results are reported.
    Keywords: NAVIGATION
    Type: NASA-CR-138453 , JPL-TM-33-683
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  • 16
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    Mariner Mars 1971 inertial reference unit (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The design concept of an inertial reference unit is reported that uses the gyroscope in a rate mode in conjunction with a unique application of a drift compensated and temperature stabilized solid state integrator for the inertial mode. A typical test program and results for an inertial reference unit as applied to the Mariner Mars 1971 program to achieve highly reliable spacecraft operation are also described.
    Keywords: NAVIGATION
    Type: NASA-CR-137356 , JPL-TM-33-662
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  • 17
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    In flight ground control of high drag satellites utilizing on-board accelerometer data and rapid orbit prediction techniques (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: High drag satellites frequently require precise verification of orbital maneuvers and the accurate prediction of perigee height. An in-flight ground support system designed to monitor and compute orbital state and maneuvers is described. The use of on-board three-axis accelerometer data in a flight support software system to perform on-line maneuver analysis and atmospheric model updating is discussed. In addition, automated analytic techniques to rapidly and accurately predict perigee height following a maneuver are described, as well as semianalytic averaging techniques designed to predict a decaying orbital state for mission control.
    Keywords: NAVIGATION
    Type: AIAA PAPER 74-809 , Mechanics and Control of Flight Conference; Aug 05, 1974 - Aug 09, 1974; Anaheim, CA
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    NASA TECHNICAL REPORTS
  • 18
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    Autonomous orbital navigation using Kepler's equation (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A simple method of determining the six elements of elliptic satellite orbits has been developed for use aboard manned and unmanned spacecraft orbiting the earth, moon, or any planet. The system requires the use of a horizon sensor or other device for determining the local vertical, a precision clock or timing device, and Apollo-type navigation equipment including an inertial measurement unit (IMU), a digital computer, and a coupling data unit. The three elements defining the in-plane motion are obtained from simultaneous measurements of central angle traversed around the planet and elapsed flight time using a linearization of Kepler's equation about a reference orbit. It is shown how Kalman filter theory may also be used to determine the in-plane orbital elements. The three elements defining the orbit orientation are obtained from position angles in celestial coordinates derived from the IMU with the spacecraft vertically oriented after alignment of the IMU to a known inertial coordinate frame.
    Keywords: NAVIGATION
    Type: AIAA PAPER 74-808 , Mechanics and Control of Flight Conference; Aug 05, 1974 - Aug 09, 1974; Anaheim, CA
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  • 19
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    Microwave landing system requirements for STOL operations (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The operational/functional requirements for the new Microwave Landing System (MLS) are examined for STOL operations. The study utilizes a nonlinear six-degree-of-freedom simulation of a De Havilland Buffalo C-8A aircraft and automatic flight control system to assess the MLS/STOL accuracy, coverage, and data rate requirements for the azimuth, DME, primary elevation, and flare elevation functions. The aircraft performance is statistically determined for representative curved flight paths through touchdown. A range of MLS errors and coverages, environmental disturbances, and navigation filtering are investigated. The study indicates that STOL applications do not place any unique requirements on the MLS.
    Keywords: NAVIGATION
    Type: AIAA PAPER 74-997 , Aircraft Design, Flight Test and Operations Meeting; Aug 12, 1974 - Aug 14, 1974; Los Angeles, CA
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    NASA TECHNICAL REPORTS
  • 20
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    Maneuver strategies for the extended Pioneer 11 Jupiter/Saturn mission (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The Jupiter-bound Pioneer 11 spacecraft was launched in April 1973, eight months before the Jupiter encounter of the front-running spacecraft, Pioneer 10. Near-Earth maneuvers placed Pioneer 11 on an interim flight path designed to retain a later retargeting capability to repeat the Pioneer 10 flyby geometry or encounter a wide variety of alternate Jupiter aimpoints, including one resulting in an extended five-year trajectory to Saturn. Pioneer 11 was retargeted to this aimpoint in April 1974, subsequent to the successful Pioneer 10 encounter in December 1973. This paper presents the retargeting and trimming maneuver strategies necessary to assure a productive Pioneer 11 Jupiter encounter in early December 1974, followed by a Saturn encounter in late 1979.
    Keywords: NAVIGATION
    Type: AIAA PAPER 74-846 , Mechanics and Control of Flight Conference; Aug 05, 1974 - Aug 09, 1974; Anaheim, CA
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    NASA TECHNICAL REPORTS
  • 21
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    Long arc orbit determination for Mariner 9 using combined radio and optical data types (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Results of postflight orbit determination for the Mariner 9 trajectory (Mariner-Mars 1971 mission) using Doppler data combined with optical data in the form of TV photographs of the natural satellites and Mars' surface features. It is shown that the combined data yield a solution which is a factor of 3 to 5 better than that obtained from Doppler-only solutions for the node of the orbit relative to the plane perpendicular to the Earth-Mars line. Consequently, these optical data types have a demonstrated potential to significantly improve planetary orbiter navigation accuracies.
    Keywords: NAVIGATION
    Type: AIAA PAPER 74-829 , Mechanics and Control of Flight Conference; Aug 05, 1974 - Aug 09, 1974; Anaheim, CA
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  • 22
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    Use of ballistic arcs for low thrust navigation enhancement in the 1980 Encke slow flyby (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A technique is presented for improving navigation accuracy in the Solar Electric Encke Slow Flyby Mission proposed to encounter the comet Encke during its 1980 apparition. The effect of the dominant navigation error source, the high level thruster noise, is reduced through the introduction of a ballistic coast arc for the purpose of orbit determination enhancement. The placement and duration of the arc is investigated with respect to its impact on final delivery error and on control effort required for trajectory correction. Also examined are the changes in delivery accuracy and control effort as a result of the time lag between the state estimation process and the thrust control program update.
    Keywords: NAVIGATION
    Type: AIAA PAPER 74-828 , Mechanics and Control of Flight Conference; Aug 05, 1974 - Aug 09, 1974; Anaheim, CA
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  • 23
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    Description and flight performance of two systems for two-segment approach (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper describes two different avionic systems which were designed and developed to provide guidance and control for two-segment noise abatement approaches. The concept of a low-cost retrofit avionic system evolved into a special-purpose two-segment computer which required a DME collocated with the ILS glide-slope transmitter. This system was evaluated in a Boeing 727-200 aircraft. The second system is an area navigation (RNAV) system modified to include the two-segment approach. This system is more sophisticated than the first system and does not restrict usage to any specific navigation ground aid. The modified RNAV system is a Collins ANS-70A and is currently being evaluated in a DC-8-61 aircraft.
    Keywords: NAVIGATION
    Type: AIAA PAPER 74-980 , Aircraft Design, Flight Test and Operations Meeting; Aug 12, 1974 - Aug 14, 1974; Los Angeles, CA
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  • 24
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    A study of Space Shuttle approach and landing navigation with conventional navaids (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Four candidate navigation systems for the Space Shuttle Orbiter approach and landing phase are evaluated in detail. These include three conventional navaid systems and a single-station one-way Doppler system. In each case a Kalman filter is assumed to be mechanized in the onboard computer, blending the navaid data with IMU and altimeter data. Filter state dimensions ranging from 6 to 24 are involved in the candidate systems. Comprehensive truth models with state dimensions ranging from 63 to 82 are formulated and used to generate detailed performance projections. The detailed results are summarized, compared, and interpreted, the filter designs are reviewed, and suggestions are made concerning possible software improvements.
    Keywords: NAVIGATION
    Type: National Aerospace Meeting; Mar 12, 1974 - Mar 13, 1974; Dayton, OH
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  • 25
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    Influence of precision inertial systems on astronomical observations (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The incorporation of precision inertial control on LST could exert a strong influence on the philosophy of and techniques for carrying out astronomical observations. In conjunction with a fine guidance star sensor, the inertial reference unit (IRU) described herein could easily expand LST capability to include observations such as (1) tracking of solar system objects, including specific points of interest on the planets; (2) rapid repositioning of scanning sensors on distributed objects such as nebulae and galaxies; (3) carrying out unified star catalog measurements to eliminate the overlap problem which exists in all ground procedures; and (4) carrying out various astrometric measurements with 'real time' data reduction capability.
    Keywords: NAVIGATION
    Type: AIAA PAPER 74-876 , Mechanics and Control of Flight Conference; Aug 05, 1974 - Aug 09, 1974; Anaheim, CA
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  • 26
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    Conditioning of MVM '73 radio-tracking data (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An extensive effort was undertaken to edit Mariner 10 radiometric tracking data. Interactive computer graphics were used for the first time by an interplanetary mission to detect blunder points and spurious signatures in the data. Interactive graphics improved the former process time by a factor of 10 to 20, while increasing reliability. S/X dual Doppler data was used for the first time to calibrate charged particles in the tracking medium. Application of the charged particle calibrations decreased the orbit determination error for a short data arc following the 16 March 1974 maneuver by about 80%. A new model was developed to calibrate the earth's troposphere with seasonal adjustments. The new model has a 2% accuracy and is 5 times better than the old model.
    Keywords: NAVIGATION
    Type: AIAA PAPER 74-832 , Mechanics and Control of Flight Conference; Aug 05, 1974 - Aug 09, 1974; Anaheim, CA
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    NASA TECHNICAL REPORTS
  • 27
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    Multiple target tracking and target attitude determination with a scanning laser radar (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A scanning laser radar that can acquire and track single or multiple targets has recently been developed. Scan patterns have been designed for acquisition and tracking of one or more targets using a narrow laser beam. A synchronously scanned transmitter-receiver is used to acquire and track targets anywhere in a 376 x 376 element raster covering a 30 x 30 deg field. All scan patterns are electronically programmed, and the system automatically acquires and tracks the target or targets without the aid of an operator. The maximum tracking rate is 1.0 deg/sec (10.0 deg/sec) when used with a 1 kHz (10 kHz) scan rate. The estimated free space range against passive cooperative targets (corner cube reflectors) is 30 nautical miles. The laser radar has an accuracy of 10 cm (range) and 0.05 deg (angle). The developmental system is relatively small (1.5 cu ft), lightweight (60 lbs) and low-power-consuming (60 W).
    Keywords: NAVIGATION
    Type: National Aerospace Meeting; Mar 12, 1974 - Mar 13, 1974; Dayton, OH
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  • 28
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    Navigation of the Mariner 10 spacecraft to Venus and Mercury (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Orbit determination techniques used during the highly successful flight of Mariner 10 to Venus and Mercury are presented. Comparisons are made between different data sets, different sets of parameters, and between a conventional least squares batch filter and a sequential batch filter and smoother that was designed for this mission. The sequential filter was able to account for small spacecraft forces that the batch filter was unable to handle effectively, and hence, contributed greatly to the mission success. The sequential filter and smoother design is given as well as results for each phase of the mission.-
    Keywords: NAVIGATION
    Type: AIAA PAPER 74-844 , Mechanics and Control of Flight Conference; Aug 05, 1974 - Aug 09, 1974; Anaheim, CA
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    NASA TECHNICAL REPORTS
  • 29
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    Resume of the status and benefits of the two-segment approach and its applicability to the jet transport fleet (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: NASA, in cooperation with the FAA, is evaluating the two-segment approach as a routine procedure for reducing aircraft noise. The program calls for separate flight evaluations using a 727 and a DC-8, and an extrapolation of these results to determine the adaptability of the technique to the rest of the fleet. The total program is reviewed. The profile and procedures developed and the noise reduction achievable are presented. The vortex characteristics behind an aircraft on a two-segment path is covered. Finally, cost estimates for retrofitting aircraft with two-segment avionics are presented.
    Keywords: NAVIGATION
    Type: AIAA PAPER 74-978 , Aircraft Design, Flight Test and Operations Meeting; Aug 12, 1974 - Aug 14, 1974; Los Angeles, CA
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    Rigid body mode pointing accuracy and stability criteria for an orbiting spacecraft (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The effect of gravity gradient torque disturbances (which is an order of magnitude greater than the other torque disturbances and is sinusoidal with a frequency of two cycles per orbit) on pointing accuracy can be predicted very precisely. However, since the sensor noise such as star tracker and gyro inherent noise, is random, their effect can only be predicted statistically. The most common method used is computer simulation with appropriate sensor model and adjusting spacecraft control laws for minimum pointing error, as presented by Harris (1972). The general investigation outlined theoretically relates spacecraft controls to pointing accuracy in terms of the sensor noise power spectrum. The results are presented in graphical form.
    Keywords: NAVIGATION
    Type: Journal of Spacecraft and Rockets; 11; Aug. 197
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  • 31
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    The navigation of space probes (1974)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: A new navigational method combining electronic measurement procedures and celestial mechanics makes it possible to conduct a space probe very close to a desired point in the neighborhood of a remote planet. Approaches for the determination of the position of the space probe in space are discussed, giving attention to the effects of errors in the employed data. The application of the navigational methods in a number of space missions is also considered.
    Keywords: NAVIGATION
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  • 32
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    Optimal guidance for the space shuttle transition (1974)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: A guidance method for the space shuttle's transition from hypersonic entry to subsonic cruising flight is presented. The method evolves from a numerical trajectory optimization technique in which kinetic energy and total energy (per unit weight) replace velocity and time in the dynamic equations. This allows the open end-time problem to be transformed to one of fixed terminal energy. In its ultimate form, E-Guidance obtains energy balance (including dynamic-pressure-rate damping) and path length control by angle-of-attack modulation and cross-range control by roll angle modulation. The guidance functions also form the basis for a pilot display of instantaneous maneuver limits and destination. Numerical results illustrate the E-Guidance concept and the optimal trajectories on which it is based.
    Keywords: NAVIGATION
    Type: Journal of Spacecraft and Rockets; 11; Mar. 197
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  • 33
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    Standardized strapdown inertial component modularity study, volume 2 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: To obtain cost effective strapdown navigation, guidance and stabilization systems to meet anticipated future needs a standardized modularized strapdown system concept is proposed. Three performance classes, high, medium and low, are suggested to meet the range of applications. Candidate inertial instruments are selected and analyzed for interface compatibility. Electronic packaging and processing, materials and thermal considerations applying to the three classes are discussed and recommendations advanced. Opportunities for automatic fault detection and redundancy are presented. The smallest gyro and accelerometer modules are projected as requiring a volume of 26 cubic inches and 23.6 cubic inches, respectively. Corresponding power dissipation is projected as 5 watts, and 2.6 watts respectively.
    Keywords: NAVIGATION
    Type: NASA-CR-120428 , R-826-VOL-2
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  • 34
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    Evaluation of selected strapdown inertial instruments and pulse torque loops, volume 1 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Design, operational and performance variations between ternary, binary and forced-binary pulse torque loops are presented. A fill-in binary loop which combines the constant power advantage of binary with the low sampling error of ternary is also discussed. The effects of different output-axis supports on the performance of a single-degree-of-freedom, floated gyroscope under a strapdown environment are illustrated. Three types of output-axis supports are discussed: pivot-dithered jewel, ball bearing and electromagnetic. A test evaluation on a Kearfott 2544 single-degree-of-freedom, strapdown gyroscope operating with a pulse torque loop, under constant rates and angular oscillatory inputs is described and the results presented. Contributions of the gyroscope's torque generator and the torque-to-balance electronics on scale factor variation with rate are illustrated for a SDF 18 IRIG Mod-B strapdown gyroscope operating with various pulse rebalance loops. Also discussed are methods of reducing this scale factor variation with rate by adjusting the tuning network which shunts the torque coil. A simplified analysis illustrating the principles of operation of the Teledyne two-degree-of-freedom, elastically-supported, tuned gyroscope and the results of a static and constant rate test evaluation of that instrument are presented.
    Keywords: NAVIGATION
    Type: NASA-CR-120427 , R-826-VOL-1
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  • 35
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    Long-duration life tests of slip ring capsule assemblies for inertial guidance platforms (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Eight slip ring capsules, each having 80 or 100 circuits, were operated for time periods ranging from 14,300 hours to 24,700 hours. The test mode simulated the motion of gimbal axes of the Saturn inertial guidance the platform in an organic free nitrogen environment. Computer-compiled noise data (approximately 45,000 recordings) were graphed as a function of test time and position within the capsules and as extreme probability distributions. Greater than ninety-nine percent of the noise measurements for the capsules with sufficient lubrication were less than 10 milliohms. Capsules with glass dielectrics did not perform significantly differently than those with filled epoxy dielectrics. The initial wear mode of prow formation was followed by rider wear. After 10 to the 8th power wipes, ring wear depth did not exceed the surface finish and the radial rider wear depth was less than 13 microns.
    Keywords: NAVIGATION
    Type: NASA-CR-138948 , MO-16673
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  • 36
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    Preliminary study of a possible automatic landing system (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Navigation and control laws for a possible automatic landing system have been investigated. The system makes use of data from an inertial table and either an airborne or ground radar to generate signals that guide the airplane to a landing. All landing maneuvers take place within a zone that extends 6000 m out from the touchdown point, 4000 m on each side of the runway center line, and 540 m high. The results show that the system can adequately control the airplane on steep, curved decelerating approaches to a landing that takes place with small errors from the desired landing point and desired airplane attitude. The system studied would interface well with the scanning beam microwave landing system (MLS). The use of this system with the MLS makes it possible to incorporate an independent landing monitor.
    Keywords: NAVIGATION
    Type: NASA-TN-D-7611 , L-9246
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  • 37
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    SIRU utilization. Volume 1: Theory, development and test evaluation (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The theory, development, and test evaluations of the Strapdown Inertial Reference Unit (SIRU) are discussed. The statistical failure detection and isolation, single position calibration, and self alignment techniques are emphasized. Circuit diagrams of the system components are provided. Mathematical models are developed to show the performance characteristics of the subsystems. Specific areas of the utilization program are identified as: (1) error source propagation characteristics and (2) local level navigation performance demonstrations.
    Keywords: NAVIGATION
    Type: NASA-CR-138574 , R-747-VOL-1
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  • 38
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    Vehicle misalignment prediction and vehicle/experiment pointing compatibility assessment (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A technique for predicting vehicle misalignment, the relationship of vehicle misalignment to the total vehicle/experiment integration effort, and the methodology used in performing a vehicle/experiment pointing compatibility assessment, are presented. The technique is demonstrated in detail by describing how it was used on the Skylab Program.
    Keywords: NAVIGATION
    Type: NASA-TM-X-64840
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  • 39
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    Development and flight tests of a gyro-less wing leveler and directional autopilot (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A gyro-less wing leveler and directional autopilot were developed and flight tested in a single-engine light airplane. The primary purpose of the project was to develop a simple, reliable, low-cost stability augmentation and autopilot system for light aircraft. The wing leveler used a fluidic inertial rate sensor, electronic signal processing circuitry, and vacuum operated servos. A strap-down magnetic heading reference of simple design provided the wing leveler with directional autopilot capability. Flight tests indicated that the performance of the gyro-less wing leveler was equal to that of a commercial wing leveler using a gyroscopic rate sensor. Drift-free, long-term, heading-hold capability of the magnetic heading reference was demonstrated.
    Keywords: NAVIGATION
    Type: NASA-TN-D-7460 , L-9229
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  • 40
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    A strapdown laser gyro navigator (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A broad spectrum of commercial and military vehicles employ some form of inertial measurement equipment. In general this equipment has a special purpose in that it was tailored for each specific application thereby resulting in high installation and maintenance costs. Recently the emphasis has been directed toward developing low cost building blocks from which the desired inertial functions can be derived. This paper describes a National Aeronautics and Space Administration (NASA) program that combines inertial system sensor and computational advances into a flight demonstration configuration. Specifically, an inertial navigation system employing strapdown laser gyro angular rate sensors and a miniature, modular digital flight computer is described. The objective of this program is to demonstrate, via flight test evaluation, the capabilities of the advanced sensor and computer as they apply to future low cost, high reliability inertial system applications.
    Keywords: NAVIGATION
    Type: NAECON ''74; National Aerospace and Electronics Conference; May 13, 1974 - May 15, 1974; Dayton, OH
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  • 41
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    New development in high reliability strapdown platforms using TDF sensors (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: New development in high reliability strapdown navigation platform using two-degree-of-freedom sensors and redundancy concept is presented in this paper. The development is based on the assumption that each axis of the sensor can fail without affecting the remaining axis. The systems reliability is investigated, the optimum redundancy configurations are proposed, a technique of sensor performance management is developed for the proposed systems.
    Keywords: NAVIGATION
    Type: Joint Automatic Control Conference; Jun 18, 1974 - Jun 21, 1974; Austin, TX
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  • 42
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    Simulation and flight evaluation of a heads-up display for general aviation (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A landing-site indicator (LASI) has been devised as a relatively simple heads-up display to show the pilot the magnitude and direction of the aircraft's velocity vector superimposed on the pilot's view of the landing area. A total of 160 landings were performed in a fixed-base simulation program by four pilots with and without the LASI display. These tests showed the display to be of beneficial use in making the approaches more consistent. Some inferences were also made that the physical workload would also be less with its use. The pilots generally agreed that the LASI, as represented in the simulation was a useful landing aid. Additional pilot comments from preliminary flight tests of a breadboard LASI display unit tend to confirm the simulator results.
    Keywords: NAVIGATION
    Type: SAE PAPER 740347 , Business Aircraft Meeting; Apr 02, 1974 - Apr 05, 1974; Wichita, KS
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  • 43
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    Design of a GN and C system to meet reliability goals (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper analyzes the reliability of the guidance, navigation, and control (GNC) portion of an avionics system for the Space Shuttle Orbiter. This analysis shows how the GNC design is affected by the need to achieve an acceptable probability of successful completion of a mission and of safe return to an airport. It varies the redundancy of the inertial measurement unit (IMU), computers, and other time-critical elements. It also includes the reliability of the flight control electronics and of the nontime-critical sensors on a phase-by-phase basis. It shows that quadruple redundancy in certain subsystems, high quality parts, and cross-strapping on orbit are required.
    Keywords: NAVIGATION
    Type: Annual Reliability and Maintainability Symposium; Jan 29, 1974 - Jan 31, 1974; Los Angeles, CA
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  • 44
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    Maneuver analysis (1973)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: The maneuver analysis for the Mariner 9 mission, both prelaunch and in-flight, was different from that of previous Mariners because of the requirement to insert the spacecraft into orbit about Mars and to trim the orbit to an unprecedented accuracy. The most apparent differences were in the spacecraft design, the software development, and the maneuver strategy required for each phase of the mission. The analysis that was performed and the software that was developed, with emphasis on the maneuver strategy and actual in-flight results are described.
    Keywords: NAVIGATION
    Type: Its Mariner 9 Navigation; p 193-217
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  • 45
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    Introduction (1973)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: A description is given of the navigation of Mariner 9, which included not only precision flight path control but also pointing of the scientific instruments mounted on a two-degree of freedom scan platform. Flight path control involved the determination of the spacecraft trajectory and the design and execution of the propulsive maneuvers required to effect the necessary changes in the trajectory. Radiometric tracking data provided by the Deep Space Network (DSN) were the principal data type used in the orbit determination process. During the Mars approach phase, optical tracking data were also used, but only on an experimental basis.
    Keywords: NAVIGATION
    Type: Mariner 9 Navigation; p 1-19
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  • 46
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    Omega windfinding system designed to meet accuracy requirements of GARP Atlantic Tropical Experiment (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Illustrations of high sferics content Omega data are presented and techniques for recovering the true Omega phase data are discussed. A description is given of the design and the operation of the hardware preprocessor developed to extract the true Omega phase data from the received signals. The software developed to compute upper-air winds from high sferics content data is discussed together with the program conducted to establish the validity of the system.
    Keywords: NAVIGATION
    Type: American Meteorological Society; vol. 54
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  • 47
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    A star sensor for attitude determination (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Description of the optical and electronic characteristics of a star sensor developed for the Small Astronomy Satellite B. The specified design goals of the star sensor included an accuracy of 3 arc minutes. Results from field tests and operation in orbit are presented.
    Keywords: NAVIGATION
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  • 48
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    Rotations about nonorthogonal axes. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Given a desired three-axis reorientation, it is well known that there are, in general, twelve possible sequences of three successive rotations about orthogonal axes which will perform the reorientation. The present paper determines whether the maneuver can or cannot be accomplished with three successive rotations aobut arbitrary (not necessarily orthogonal) axes. This result is then employed to derive conditions on the axes which insure that every rotation may be so generated. The associated angles of all the possible three-legged slews are exhibited by a closed analytical procedure which requires no assumptions concerning the degree of nonorthogonality nor any approximations. The classical orthogonal case (Euler angles) is then an immediate consequence as a special case of the generalized solution.
    Keywords: NAVIGATION
    Type: AIAA Journal; 11; June 197
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  • 49
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    An analytic study of near terminal area optimal sequencing and flow control techniques (1973)
    In:  CASI
    Details
    Publication Date: 2012-05-23
    Description: Optimal flow control and sequencing of air traffic operations in the near terminal area are discussed. The near terminal area model is based on the assumptions that the aircraft enter the terminal area along precisely controlled approach paths and that the aircraft are segregated according to their near terminal area performance. Mathematical models are developed to support the optimal path generation, sequencing, and conflict resolution problems.
    Keywords: NAVIGATION
    Type: AGARD Air Traffic Control Systems; 18 p
    Format: text
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  • 50
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    Progress in strapdown technology (1973)
    In:  CASI
    Details
    Publication Date: 2012-05-23
    Description: An overview is presented of typical inertial grade instrumentation available to mechanize precision strapdown attitude reference systems as well as a novel scheme of redundancy management, if two degree of freedom instruments are used. The instrumentation is divided between conventional and unconventional sensors with some assessment of their readiness included.
    Keywords: NAVIGATION
    Type: AGARD Inertial Navigation Components and Systems; 9 p
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  • 51
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    Failure management of multiple gimbal inertial systems for space shuttle (1973)
    In:  CASI
    Details
    Publication Date: 2012-05-23
    Description: A failure detection and isolation technique for use with four gimbaled inertial measurement units (IMU) is presented. By using simulated boost and entry shuttle trajectories with specific gimbaled IMU models, failure detection thresholds are developed based on red-line life dependent requirements and warning thresholds within the red-line thresholds based on expected worst case IMU performance. Using these trajectories, established trajectory threshold, and multiple IMU models, various failure detection and isolation techniques are evaluated for application in both powered and unpowered flight phases. The adequacy of the systems for both attitude and velocity detection methods is evaluated and recommendations for space shuttle applications are made.
    Keywords: NAVIGATION
    Type: AGARD Inertial Navigation Components and Systems; 14 p
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  • 52
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    Spacecraft reorientation via slewing about nonorthogonal axes (1973)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A mathematical procedure was developed which determines the exact slews relative to any known axes. The axes may be completely arbitrary; their coordinates merely reside on a data base which can be changed at any time without affecting the software. Given the desired reorientation, the procedure then determines all of the two-legged or three-legged slews which will accomplish the reorientation. For example, there are 12 possible permutations of three axes, and if they are orthogonal each always has two solutions. The nonorthogonal case, on the other hand, gives some surprising results, including the nonexistence of a solution: Consider a large reorientation where the three axes are nearly collinear. In this connection, it can be shown that every three-axis reorientation can be accomplished by three successive slews, if and only if the middle axis is perpendicular to the other two.
    Keywords: NAVIGATION
    Type: Significant Accomplishments in Technol., 1972; p 140-142
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  • 53
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    Fine pointing control, OAO-3 (1973)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The fine error sensor located within the Princeton Experiment Package (PEP) is designed to aquire a star within its field of view to hold the spacecraft within plus or minus one-tenth of an arc second in pitch, and plus or minus three-arc seconds about the yaw axis. Pointing accuracy and stability tests of the fine error sensor exceeded the plus or minus 0.1 arc second requirement.
    Keywords: NAVIGATION
    Type: Significant Accomplishments in Technol., 1972; p 22-24
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  • 54
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    Delta launch vehicle inertial guidance system (DIGS) (1973)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The Delta inertial guidance system, part of the Delta launch vehicle improvement effort, has been flown on three launches and was found to perform as expected for a variety of mission profiles and vehicle configurations.
    Keywords: NAVIGATION
    Type: Significant Accomplishments in Technol.; p 14-15
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  • 55
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    STRAP 4 sounding rocket attitude control system (1973)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A sounding rocket attitude control system is reported that uses rate integrated gyros operating in both closed loop and open loop modes at very low drift rates. In normal operation the gyros are zeroed on a nearby star and torqued to the proper location in the closed loop mode; rate output is electronically integrated to provide a position displacement signal. Once closed loop torquing is completed, the caging loop is opened and the gyro is operated as angular displacement sensor to provide limit cycle control while viewing the target.
    Keywords: NAVIGATION
    Type: Significant Accomplishments in Technol., 1972; p 16-19
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  • 56
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    Inertial reference unit (1973)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The inertial reference unit is a high performance gyro attitude reference system for use on the OAO spacecraft. The IRU is a three axis system, which provides both rate and attitude information for spacecraft control. The purpose of the IRU is to reduce the dependency on gimballed startrackers and, in turn, simplify the OAO ground operations by eliminating the need for the continual programming of gimballed startracker assignments in accordance with computed occultation schedules. During normal operations, it is used to control the pitch and yaw axes during experiment occultations and during spacecraft reorientations. The roll axis is continuously under control of the IRU except during brief periods for attitude update. To provide for these capabilities the IRU must be able to perform two basic functions. One is to maintain an inertially fixed reference for spacecraft control and the second is to accurately reorient the reference upon command.
    Keywords: NAVIGATION
    Type: Significant Accomplishments in Technol., 1972; p 20-21
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  • 57
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    En route position and time control of aircraft using Kalman filtering of radio aid data (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Fixed-time-of-arrival (FTA) guidance and navigation is investigated as a possible technique capable of operation within much more stringent en route separation standards and offering significant advantages in safety, higher traffic densities, and improved scheduling reliability, both en route and in the terminal areas. This study investigated the application of FTA guidance previously used in spacecraft guidance. These FTA guidance techniques have been modified and are employed to compute the velocity corrections necessary to return an aircraft to a specified great-circle reference path in order to exercise en route time and position control throughout the entire flight. The necessary position and velocity estimates to accomplish this task are provided by Kalman filtering of data from Loran-C, VORTAC/TACAN, Doppler radar, radio or barometric altitude,and altitude rate. The guidance and navigation system was evaluated using a digital simulation of the cruise phase of supersonic and subsonic flights between San Francisco and New York City, and between New York City and London.
    Keywords: NAVIGATION
    Type: NASA-TN-D-7509
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  • 58
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    Investigation into the propagation of Omega very low frequency signals and techniques for improvement of navigation accuracy including differential and composite omega (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An analysis of Very Low Frequency propagation in the atmosphere in the 10-14 kHz range leads to a discussion of some of the more significant causes of phase perturbation. The method of generating sky-wave corrections to predict the Omega phase is discussed. Composite Omega is considered as a means of lane identification and of reducing Omega navigation error. A simple technique for generating trapezoidal model (T-model) phase prediction is presented and compared with the Navy predictions and actual phase measurements. The T-model prediction analysis illustrates the ability to account for the major phase shift created by the diurnal effects on the lower ionosphere. An analysis of the Navy sky-wave correction table is used to provide information about spatial and temporal correlation of phase correction relative to the differential mode of operation.
    Keywords: NAVIGATION
    Type: NASA-CR-132276
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  • 59
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    New mechanization equations for aided inertial navigation systems (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Inertial navigation equations are developed which use area navigation (RNAV) waypoints and runway references as coodinate centers. The formulation is designed for aided inertial navigation systems and gives a high numerical accuracy through all phases of flight. A new formulation of the error equations for inertial navigation systems is also presented. This new formulation reduces numerical calculations in the use of Kalman filters for aided inertial navigation systems.
    Keywords: NAVIGATION
    Type: NASA-CR-2352
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  • 60
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    Space shuttle GN and C equation document: Entry and transition guidance (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The entry-guidance routine presented is designed to take the orbiter vehicle from entry interface through the critical heating phase of entry down to the start of the approach phase. The material includes: (1) a functional flow diagram, (2) input and output variables, (3) a description of equations, and (4) detailed flow diagrams.
    Keywords: NAVIGATION
    Type: NASA-CR-134148 , DOC-17-REV-3
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  • 61
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    Strapdown system Performance Optimization Test evaluations (SPOT), volume 2 (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A three axis inertial system is packaged in an Apollo gimbal fixture for fine grain evaluation of strapdown system performance in dynamic environments. These evaluations have provided information to assess the effectiveness of real-time compensation techniques and to study system performance tradeoffs to factors such as quantization iteration rate. The strapdown performance and tradeoff studies conducted in this program are discussed.
    Keywords: NAVIGATION
    Type: NASA-CR-136083 , R-743-VOL-2
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  • 62
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    Lunar Roving Vehicle Navigation System Performance Review (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The design and operation of the lunar roving vehicle (LRV) navigation system are briefly described. The basis for the premission LRV navigation error analysis is explained and an example included. The real time mission support operations philosophy is presented. The LRV navigation system operation and accuracy during the lunar missions are evaluated.
    Keywords: NAVIGATION
    Type: NASA-TN-D-7469 , M-219
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    Preliminary assessment of the microwave landing system requirements for STOL operations (1973)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: The results of an investigation made to assess the Microwave Landing System (MLS) Requirements for use by civil STOL aircraft are described. The principal MLS characteristics investigated in the report were signal accuracy and volume of coverage. The study utilized a nonlinear six-degree-of-freedom digital simulation of a De Havilland Buffalo C-8A aircraft. Fully automatic control of timed curve flight down to touchdown was simulated. Selected MLS accuracy and coverage parameters for the azimuth, primary elevation, flare evelation and DME signals were varied. The resulting STOL aircraft system performance in following a representative curved flight path was statistically determined. Coverage requirements for STOL aircraft operating in the terminal area environment were also investigated.
    Keywords: NAVIGATION
    Type: NASA-TM-X-62310
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    SIRU development. Volume 1: System development (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A complete description of the development and initial evaluation of the Strapdown Inertial Reference Unit (SIRU) system is reported. System development documents the system mechanization with the analytic formulation for fault detection and isolation processing structure; the hardware redundancy design and the individual modularity features; the computational structure and facilities; and the initial subsystem evaluation results.
    Keywords: NAVIGATION
    Type: NASA-CR-136033 , R-746-VOL-1
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    High-reliability strapdown platforms using two-degree-of-freedom gyros. (1973)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: This paper presents a new concept of high-reliability strapdown attitude sensing systems for space vehicles. Each system utilizes a set of redundant two-degree-of-freedom gyros. An optimum system configuration is obtained for maximum system reliability and the best measurement accuracy. Improved accuracy of the final data is obtained by using the least-square data reduction technique. Each system possesses a 'sensor performance management' feature which is capable of failure detection, faulty gyro identification, system reconfiguration, and, possibly, sensor recalibration. Improvement in reliability, as compared to other types of strapdown systems, is demonstrated. Details of the development are described in terms of a system containing four gyros.
    Keywords: NAVIGATION
    Type: IEEE Transactions on Aerospace and Electronic Systems; AES-9; Mar. 197
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  • 66
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    Ground and flight experience with a strapdown inertial measuring unit and a general purpose airborne digital computer (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Ground and flight tests were conducted to investigate the problems associated with using a strapdown inertial flight data system. The objectives of this investigation were to develop a three axis inertial attitude reference system, to evaluate a self-alignment technique, and to examine the problem of time-sharing a general purpose computer for the several tasks required of it. The performance of the strapdown platform/computer system that was developed was sufficiently accurate for the tasks attempted. For flights on the order of 45 minutes duration, attitude angle errors of + or -.035 radian (+ or -2 deg) in all axes were observed. Laboratory tests of the self-alignment technique gave accuracies of + or -.00075 radian in pitch and roll axes and + or -0.0045 radian in the yaw axis. Self-alignment flight results were inconsistent, since a stable solution was not obtained on windy days because of aircraft rocking motions.
    Keywords: NAVIGATION
    Type: NASA-TM-X-2848 , H-735
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    Development of a width-modulated pulse rebalance electronics loop for strapdown gyroscopes (1973)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: A new width modulated pulse rebalance electronics loop was developed for use with strapdown gyroscopes. Advantages of the width modulated binary over the ternary loop are the following: (1) The H-switch is easier to implement; (2) torque is applied in finely quantized increments; (3) the analog-to-digital conversion for data generation is inside the loop and is directly determined by the torque pulse; (4) on part of the loop compensation network bypasses the gyroscope; and (5) the torquer is fed constant power.
    Keywords: NAVIGATION
    Type: NASA-CR-124333 , S-25
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    Panoramic attitude sensor for Radio Astronomy Explorer-B, appendices (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see .,
    Keywords: NAVIGATION
    Type: NASA-CR-132783
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    SIRU development. Volume 3: Software description and program documentation (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The development and initial evaluation of a strapdown inertial reference unit (SIRU) system are discussed. The SIRU configuration is a modular inertial subsystem with hardware and software features that achieve fault tolerant operational capabilities. The SIRU redundant hardware design is formulated about a six gyro and six accelerometer instrument module package. The six axes array provides redundant independent sensing and the symmetry enables the formulation of an optimal software redundant data processing structure with self-contained fault detection and isolation (FDI) capabilities. The basic SIRU software coding system used in the DDP-516 computer is documented.
    Keywords: NAVIGATION
    Type: NASA-CR-128965 , R-746-VOL-3
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    Pilot's manual for automated 4D guidance system (1973)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: Operational procedures and modes of an experimental 4D guidance system are described from the pilot's point of view. The system consists of the experimental avionics equipment referred to as STOLAND and a specially developed software package for the STOLAND digital computer. A capture mode of the system provides arrival time control and automatic tracking of the 4D flight path from any feasible initial aircraft state to any waypoint. Precise arrival time at a waypoint is achieved by means of speed control or, if large delays are required, by path stretching. Continuous recomputation and display of the capture flight path prior to engaging the system permits the pilot to determine the exact moment for terminating a holding or path stretching maneuver in order to achieve a specified arrival time.
    Keywords: NAVIGATION
    Type: NASA-TM-X-62233
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    Space shuttle GN and C equation document no. 23: Energy dissipation rate guidance for approach phase (1973)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: The approach guidance routine for taking the space shuttle orbiter from the entry phase of approximately 100,000 feet to the start of the final landing maneuver is discussed. The approach guidance system is a closed feedback loop scheme. The vehicle energy is managed by controlling the rate at which energy is dissipated during a straight in approach. The spacecraft performance during each segment of the approach flight is analyzed. Equations of motion are developed to describe the spacecraft guidance and flight path.
    Keywords: NAVIGATION
    Type: NASA-CR-128960 , T73-14251
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    Navigation, guidance, and control systems for V/STOL aircraft. (1973)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: The development of digital autopilots and integrated avionics systems, applicable to many classes of vehicles and missions, was undertaken by Sperry Flight Systems in the mid-sixties. The first application of the system was planned for automatic flight control in the U.S. supersonic transport; the termination of that program, however, thwarted any flight experience. The second application, which has additional navigation and energy management functions, is an airborne simulator of the space shuttle vehicle. The latter system underwent a series of successful flight tests in a CV-990 aircraft under contract with NASA. The third application, which has new electronic displays, air data computation, and time-constrained guidance (i.e., specified position and altitude at a specified time), is in the DOT/NASA STOLAND test program. The STOLAND system is described specifically in this paper.
    Keywords: NAVIGATION
    Type: Sperry Technology; 1; 3, 19; 1973
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    Apollo LM guidance computer software for the final lunar descent. (1973)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: In all manned lunar landings to date, the lunar module Commander has taken partial manual control of the spacecraft during the final stage of the descent, below roughly 500 ft altitude. This report describes programs developed at the Charles Stark Draper Laboratory, MIT, for use in the LM's guidance computer during the final descent. At this time computational demands on the on-board computer are at a maximum, and particularly close interaction with the crew is necessary. The emphasis is on the design of the computer software rather than on justification of the particular guidance algorithms employed. After the computer and the mission have been introduced, the current configuration of the final landing programs and an advanced version developed experimentally by the author are described.
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    A guidance and navigation system for continuous low thrust vehicles (1973)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: A midcourse guidance and navigation system for continuous low thrust vehicles is described. A set of orbit elements, known as the equinoctial elements, are selected as the state variables. The uncertainties are modelled statistically by random vector and stochastic processes. The motion of the vehicle and the measurements are described by nonlinear stochastic differential and difference equations respectively. A minimum time nominal trajectory is defined and the equation of motion and the measurement equation are linearized about this nominal trajectory. An exponential cost criterion is constructed and a linear feedback guidance law is derived to control the thrusting direction of the engine. Using this guidance law, the vehicle will fly in a trajectory neighboring the nominal trajectory. The extended Kalman filter is used for state estimation. Finally a short mission using this system is simulated. The results indicate that this system is very efficient for short missions.
    Keywords: NAVIGATION
    Type: NASA-CR-138676 , TE-53
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    Feasibility test for a V-slit star mapper for pioneer spacecraft terminal navigation (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A laboratory demonstration of the feasibility of using a V-slit star mapper to meet the sensitivity and accuracy of on-board navigational requirements for future Pioneer Missions to the outer planets was conducted by the Control and Sensors Laboratory of TRW. The breadboard was extremely simple in configuration, consisting of an end-on photomultiplier tube and a V-slit reticle located at the focal plane of the objective lens. In addition, a plano-convex lens was used between the reticle and the PMT in a Fabry-Perot configuration. The analytical effort indicated that the sensor should easily meet the requirements. The Pioneer SRA test set was examined to determine its basic accuracy and modify it where necessary to bring its accuracy into the 1-3 arc second range. The test results show that it is feasible to use this type of star mapper in the 10 arc second accuracy range. The test equipment accuracy (approximately 5 arc Sec) was sufficient to bound the sensor errors at less than 10 arc seconds.
    Keywords: NAVIGATION
    Type: NASA-CR-114734 , R-7537-2-451
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  • 76
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    Spin reorientation of a nonsymmetric body with energy dissipation (1973)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: Stable rotating semi-rigid bodies were demonstrated analytically, and verified in flights such as Explorer 1 and ATS-5 satellites. The problem arises from the two potential orientations which the final spin vector can take after large angle reorientation from minor to major axis, i.e., along the positive or negative axis of the maximum inertia. Reorientation of a satellite initially spinning about the minor axis using an energy dissipation device may require that the final spin orientation be controlled. Examples of possible applications are the Apogee Motor Assembly with Paired Satellites (AMAPS) configuration, where proper orientation of the thruster is required; and reorientation of ATS-5, where the spin sensitive nature of the despin device (yo-yo mechanism) requires that the final spin vector point is a specified direction.
    Keywords: NAVIGATION
    Type: NASA-CR-131320 , ASTRONAUT-RR-73-2
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    Ames-aided inertial navigation work - The first two years of progress (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A description of work whose broad objective is to attain improved aircraft navigation performance through exploitation of the concept of combining navigation data from several sources in an optimum manner is presented. The system developed as a result of the work, called RAINPAL (Recursive Aided Inertial Navigation for Precision Approach and Landing) is designed to combine precision radio range measurements with data from on-board inertial sensors to achieve precision navigation for approach and landing. The paper describes RAINPAL and the rationale of its design, and also serves as a sort of planning document, including a progress report, a summary of objectives past and present, and an exposition of reasons for doing the work.
    Keywords: NAVIGATION
    Type: NASA-TM-X-62199
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    Competitive evaluation of failure detection algorithms for strapdown redundant inertial instruments (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Algorithms for failure detection, isolation, and correction of redundant inertial instruments in the strapdown dodecahedron configuration are competitively evaluated in a digital computer simulation that subjects them to identical environments. Their performance is compared in terms of orientation and inertial velocity errors and in terms of missed and false alarms. The algorithms appear in the simulation program in modular form, so that they may be readily extracted for use elsewhere. The simulation program and its inputs and outputs are described. The algorithms, along with an eight algorithm that was not simulated, also compared analytically to show the relationships among them.
    Keywords: NAVIGATION
    Type: NASA-CR-124234 , TRW-18313-6004-RU-00
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    Air traffic control surveillance accuracy and update rate study (1973)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: The results of an air traffic control surveillance accuracy and update rate study are presented. The objective of the study was to establish quantitative relationships between the surveillance accuracies, update rates, and the communication load associated with the tactical control of aircraft for conflict resolution. The relationships are established for typical types of aircraft, phases of flight, and types of airspace. Specific cases are analyzed to determine the surveillance accuracies and update rates required to prevent two aircraft from approaching each other too closely.
    Keywords: NAVIGATION
    Type: NASA-CR-139043 , TRW-18618-6004-RU-00
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    Study of effects of uncertainties on comet and asteroid encounter and contact guidance requirements. Part 1: Guidance and navigation studies (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A guidance algorithm that provides precise rendezvous in the deterministic case while requiring only relative state information is developed. A navigation scheme employing only onboard relative measurements is built around a Kalman filter set in measurement coordinates. The overall guidance and navigation procedure is evaluated in the face of measurement errors by a detailed numerical simulation. Results indicate that onboard guidance and navigation for the terminal phase of rendezvous is possible with reasonable limits on measurement errors.
    Keywords: NAVIGATION
    Type: NASA-CR-120329
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    A comparative analysis of area navigation systems in general aviation (1973)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: Radio navigation systems which offer the capabilities of area navigation to general aviation operators are discussed. The systems considered are: (1) the VORTAC system, (2) the Loran-C system, and (3) the Differential Omega system. The inital analyses are directed toward a comparison of the systems with respect to their compliance to specified performance parameters and to the cost effectiveness of each system in relation to those specifications. Further analyses lead to the development of system cost sensitivity charts, and the employment of these charts allows conclusions to be drawn relative to the cost-effectiveness of the candidate navigation system.
    Keywords: NAVIGATION
    Type: NASA-CR-132504 , FTL-R74-1
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    Asymptotic stability and instability of large-scale systems (1973)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: The purpose of this paper is to develop new methods for constructing vector Lyapunov functions and broaden the application of Lyapunov's theory to stability analysis of large-scale dynamic systems. The application, so far limited by the assumption that the large-scale systems are composed of exponentially stable subsystems, is extended via the general concept of comparison functions to systems which can be decomposed into asymptotically stable subsystems. Asymptotic stability of the composite system is tested by a simple algebraic criterion. By redefining interconnection functions among the subsystems according to interconnection matrices, the same mathematical machinery can be used to determine connective asymptotic stability of large-scale systems under arbitrary structural perturbations.
    Keywords: NAVIGATION
    Type: IEEE Transactions on Automatic Control; AC-18; Dec. 197
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    Mariner 9 navigation (1973)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: A final, comprehensive description of the navigation of Mariner 9-the first U.S. spacecraft to orbit another planet is provided. The Mariner 9 navigation function included not only precision flight path control but also pointing of the spacecraft's scientific instruments mounted on a two degree of freedom scan platform. To the extent appropriate, each section describes the perflight analyses on which the operational strategies and performance predictions were based. Inflight results are then discussed and compared with the preflight predictions. Postflight analyses, which were primarily concerned with developing a thorough understanding of unexpected in-flight results, are also presented.
    Keywords: NAVIGATION
    Type: NASA-CR-139521 , JPL-TR-32-1586
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    Conic state extrapolation (1973)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: The Conic State Extrapolation Routine provides the capability to conically extrapolate any spacecraft inertial state vector either backwards or forwards as a function of time or as a function of transfer angle. It is merely the coded form of two versions of the solution of the two-body differential equations of motion of the spacecraft center of mass. Because of its relatively fast computation speed and moderate accuracy, it serves as a preliminary navigation tool and as a method of obtaining quick solutions for targeting and guidance functions. More accurate (but slower) results are provided by the Precision State Extrapolation Routine.
    Keywords: NAVIGATION
    Type: NASA-CR-134281
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    Shuttle unified navigation filter, revision 1 (1973)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: Equations designed to meet the navigation requirements of the separate shuttle mission phases are presented in a series of reports entitled, Space Shuttle GN and C Equation Document. The development of these equations is based on performance studies carried out for each particular mission phase. Although navigation equations have been documented separately for each mission phase, a single unified navigation filter design is embodied in these separate designs. The purpose of this document is to present the shuttle navigation equations in a form in which they would most likely be coded-as the single unified navigation filter used in each mission phase. This document will then serve as a single general reference for the navigation equations replacing each of the individual mission phase navigation documents (which may still be used as a description of a particular navigation phase).
    Keywords: NAVIGATION
    Type: NASA-CR-134276
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    The advanced OPLE for search and rescue (1973)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Recent technological advances have made it possible to develop an advanced OMEGA position location experiment for a global search and rescue application. This application generated some new problem areas such as the OMEGA lane ambiguity, random access, location accuracy, real time processing, and size and weight of the Search and Rescue Communication (SARCOM). This experiment will demonstrate the feasibility of instantaneous alarm and position location by using a relatively inexpensive, battery operated, three-pound package. This package can transmit the alarm and position through a synchronous satellite to a search and rescue station in less than three minutes.
    Keywords: NAVIGATION
    Type: International Telemetering Conference; Oct 09, 1973 - Oct 11, 1973; Washington, DC
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    Development of visual-display aid to air navigation (1973)
    In:  CASI
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    Publication Date: 2019-07-13
    Description: The developments are discussed in the design of a liquid-crystal, visual display, air navigation aid, which uses two VOR signals to locate the aircraft. The system concepts, liquid crystal materials, stability tests, and the electronic system are described. It is concluded that a navigational aid of this type is technically feasible, but not at the projected low cost.
    Keywords: NAVIGATION
    Type: NASA-CR-132412
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    General aviation air traffic pattern safety analysis (1973)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A concept is described for evaluating the general aviation mid-air collision hazard in uncontrolled terminal airspace. Three-dimensional traffic pattern measurements were conducted at uncontrolled and controlled airports. Computer programs for data reduction, storage retrieval and statistical analysis have been developed. Initial general aviation air traffic pattern characteristics are presented. These preliminary results indicate that patterns are highly divergent from the expected standard pattern, and that pattern procedures observed can affect the ability of pilots to see and avoid each other.
    Keywords: NAVIGATION
    Type: NASA-TM-X-69455 , PAPER-2A-4 , System Safety Soc. Symp.; Jul 17, 1973
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    Continental Land Mass Air Traffic Control (COLM ATC) (1973)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The application of various satellite systems and techniques relative to providing air traffic control services for the continental United States was studied. Three satellite configurations were reviewed. The characteristics and capabilities of the satellites are described. The study includes consideration for the various ranging waveforms, multiple access alternatives, and the power and bandwidth required as a function of the number of users.
    Keywords: NAVIGATION
    Type: NASA-CR-132831
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  • 90
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    Redundancy management of inertial systems. (1973)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The paper reviews developments in failure detection and isolation techniques applicable to gimballed and strapdown systems. It examines basic redundancy management goals of improved reliability, performance and logistic costs, and explores mechanizations available for both input and output data handling. The meaning of redundant system reliability in terms of available coverage, system MTBF, and mission time is presented and the practical hardware performance limitations of failure detection and isolation techniques are explored. Simulation results are presented illustrating implementation coverages attainable considering IMU performance models and mission detection threshold requirements. The implications of a complete GN&C redundancy management method on inertial techniques are also explored.
    Keywords: NAVIGATION
    Type: AIAA PAPER 73-852 , Guidance and Control Conference; Aug 20, 1973 - Aug 22, 1973; Key Biscayne, FL
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  • 91
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    Navigation system design for the Mariner Jupiter/Saturn Mission. (1973)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The Mariner Jupiter/Saturn Mission is described with emphasis on the navigation problems arising in attempting a Jupiter/Saturn swingby mission which includes close encounters with one or more of the natural satellites of each planet. The navigation system being designed to solve these problems is described. This system includes sub-systems for precision trajectory correction. Earth-based radiometric data, and onboard star/satellite measurements via employment of the science-imaging TV sub-system. Total system performance is discussed as measured against the mission's inherent navigation goals.
    Keywords: NAVIGATION
    Type: AIAA PAPER 73-838 , Guidance and Control Conference; Aug 20, 1973 - Aug 22, 1973; Key Biscayne, FL
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  • 92
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    Linear filtering of ballistic-entry-probe data for atmospheric reconstruction. (1973)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A Kalman-Schmidt filter is used to estimate atmospheric and trajectory parameters for entry into the Venusian atmosphere. A significantly improved version of the Landing Trajectory Reconstruction (LTR) computer program, used to obtain the estimates is described. Major improvements involve precision and linearity control of numerical differencing, corrected perturbation modeling, and incorporation of a refractivity model. Important results show that gyroscopic data are not usable with LTR, that atmospheric properties are generally well estimated for altitudes less than 100 km, and that the two LTR modes of operation are complementary in performance.
    Keywords: NAVIGATION
    Type: AIAA PAPER 73-904 , Guidance and Control Conference; Aug 20, 1973 - Aug 22, 1973; Key Biscayne, FL
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  • 93
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    2-SPEED, a single-gimbal control moment gyro attitude control system. (1973)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: In 2-SPEED (Two Scissored Pair Ensemble, Explicit Distribution) four single-gimbal control moment gyros (SGCMGs) configured into two scissored pairs are combined with an explicit distribution of angular momentum between pairs to produce a system relatively insensitive to the singularity problems which have plagued other SGCMG concepts. In this system, the singularity surfaces in momentum space degenerate to discrete curves. Further, the system permits a smooth passage through these remaining singularities with, at worst, a temporary delay while momentum redistribution takes place. Finally, CMG-out operation is possible within the full volume of the reduced momentum envelope.
    Keywords: NAVIGATION
    Type: AIAA PAPER 73-895 , Guidance and Control Conference; Aug 20, 1973 - Aug 22, 1973; Key Biscayne, FL
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    Design of a digital controller for spinning flexible spacecraft. (1973)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A new approach to digital control system design is applied to the analysis and design of a practical onboard digital attitude control system for a class of spinning vehicles characterized by a rigid body and two connected flexible appendages. The approach used is to design a continuous-data control system that will provide a satisfactory system response. Then, using the digital redesign method, a digital controller with onboard digital computer is designed to provide a digital control system whose states are similar to those of the continuous system at sampling instants. The simplicity of application of this approach is indicated by an example in which spinning Skylab parameters are used to substantiate the conclusions.
    Keywords: NAVIGATION
    Type: AIAA PAPER 73-894 , Guidance and Control Conference; Aug 20, 1973 - Aug 22, 1973; Key Biscayne, FL
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  • 95
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    Attitude control of a large flexible spacecraft using three-axis mass expulsion control. (1973)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A study of the elastic effects of large area solar arrays on attitude control of a spacecraft was conducted. It is demonstrated for sufficiently low structural frequencies that excitation of certain modes can induce instability in the pitch axis. Stiffening the arrays can eliminate the instability. However, a severe weight penalty is associated with such modification. A more efficient means of minimizing the structural interaction effects is to change the shape of the array. For stable configurations, another problem may be encountered. This is the imposition of high rates on the spacecraft bus by oscillation of the solar arrays. Since low rates are required to obtain accurate science experiment results, it is imperative that the high rate problem be resolved. This also is possible by changing the solar array configuration.
    Keywords: NAVIGATION
    Type: AIAA PAPER 73-893 , Guidance and Control Conference; Aug 20, 1973 - Aug 22, 1973; Key Biscayne, FL
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  • 96
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    Achieving ultrahigh accuracy with a body pointing CMG/RW control system. (1973)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The purpose of the Large Space Telescope (LST) program is to place a three-meter diffraction limited telescope in a 270-nautical mile orbit in order to perform astronomical observations that are not presently possible with earth bound telescopes due to atmospheric obscuration. In order to determine whether the stringent pointing requirements could be met, a complex simulation model was defined which consisted of detailed dynamic representations of control moment gyros (CMGs) and reaction wheels including their noise characteristics, dynamic sensor representations with sensor noise, shock mounts for the CMG actuators, and a detailed flexible body structural model with all significant vehicle and solar panel bending modes. On the basis of both stability and performance studies utilizing this model, it was determined that a body pointing system will meet LST requirements.
    Keywords: NAVIGATION
    Type: AIAA PAPER 73-883 , Guidance and Control Conference; Aug 20, 1973 - Aug 22, 1973; Key Biscayne, FL
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  • 97
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    A 'type one' servo explicit model following adaptive scheme. (1973)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: This paper describes 'type 1' servo techniques applied to explicit model following systems. The advantages of using these are: (1) steady-state decoupling is provided for the controlled state variables as determined by a reference input (the pilot command for example), (2) overall stability of the decoupled adaptive scheme is guaranteed, (3) a zero steady-state error for those state variables incorporating integral feedback, to a constant input reference, and (4) improved transient performance. Example calculations have been performed using a mathematical model for a typical fighter aircraft and a desired performance reference model based on satisfactory aircraft flying qualities. Numerical results are given.
    Keywords: NAVIGATION
    Type: AIAA PAPER 73-862 , Guidance and Control Conference; Aug 20, 1973 - Aug 22, 1973; Key Biscayne, FL
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  • 98
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    Precision pointing thrustor. (1973)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A satellite experiment to test the predicted relativistic precession of a gyroscope moving through a gravitational field has been under development at Stanford University for a number of years. The instruments will be located in a liquid helium bath to insure dimensional stability and to permit using superconducting types of circuitry for readout of the gyro orientation. Heat leaks in the system cause the helium to boil and the resultant helium gas is used for attitude control. The principal subject of the paper is the design and experimental evaluation of an electromagnetically actuated differential thrustor which was built and tested at Stanford University. The results are unique because most propulsion systems operate on-off in order to utilize propellant efficiently. In this case, the gas must flow continually to provide cooling, and the requirements are primarily for low power, small volume, and high reliability.
    Keywords: NAVIGATION
    Type: AIAA PAPER 73-858 , Guidance and Control Conference; Aug 20, 1973 - Aug 22, 1973; Key Biscayne, FL
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  • 99
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    Automatic control of the Skylab Astronaut Maneuvering Research Vehicle. (1973)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The two automatic control modes of the Astronaut Maneuvering Research Vehicle (AMRV) are analyzed: the control moment gyro (CMG) and the rate gyro (RG). The AMRV is an autonomous maneuvering unit which translates and rotates the pilot by means of hand-controller input commands. The CMG normal operation, desaturation, and cage/lock dynamics are described in terms of a realistic AMRV mass property configuration. No propellant is used for normal operation in the CMG mode, and the maximum rotation rate is 5 deg/sec about each AMRV axis. The RG attitude maneuvering and limit cycle submode dynamic are described in terms of the same AMRV mass property configuration.
    Keywords: NAVIGATION
    Type: AIAA PAPER 73-857 , Guidance and Control Conference; Aug 20, 1973 - Aug 22, 1973; Key Biscayne, FL
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  • 100
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    Competitive evaluation of failure detection algorithms for strapdown redundant inertial instruments. (1973)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Seven algorithms for failure detection, isolation, and correction of strapdown inertial instruments in the dodecahedron configuration are competitively evaluated by means of a digital computer simulation that provides them with identical inputs. Their performance is compared in terms of orientation errors and computer burden. The analytical foundations of the algorithms are presented. The features that are found to contribute to superior performance are use of a definite logical structure, elimination of interaction between failures, different thresholds for first and second failures, use of the 'parity' test signals, and avoidance of iteration loops.
    Keywords: NAVIGATION
    Type: AIAA PAPER 73-853 , Guidance and Control Conference; Aug 20, 1973 - Aug 22, 1973; Key Biscayne, FL
    Format: text
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