Deep space communication.
Time reference standard, two-way doppler, ground and spacecraft antennas, circuit noise reduction and spacecraft acquisition considered in signal transmission from deep space
SPACE COMMUNICATION↗
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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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The space revolution NASA News Release
Comparison of ultimate load carrying capacity of laterally restrained/unrestrained, reinforced/unreinforced cement mortar model beams and two-way panels
INDUSTRY↗
MO BIDIC - Teletype Interface
Device for enabling two-way communication between twin digital computer and teletypewriter
COMMUNICATION SYSTEM↗
Optimum conical bodies for grazing hyperbolic entry.
Thermal phase noise and VCO effects at ground receiver output of coherent two-way Doppler communication system
THERMAL NOISE↗
Solenoid valve design minimizes vibration and sliding wear problem
Two-way cryogenic solenoid valve resists damage from vibration and metallic interfacial sliding. The new system features a flat-faced armature guided by a flexure disk which eliminates sliding surfaces and is less subject to contamination and wear.
Gillon, W. A., Jr.↗
Space Programs Summary No. 37-42, Volume III FOR the Period September 1, 1966 to October 31, 1966. Deep Space Network
The Deep Space Network (DSN), established by the NASA Office of Tracking and Data Acquisition, is under the system management and technical direction of JPL. The DSN is responsible for two-way communications with unmanned spacecraft travelling from approximately 10,000 miles from Earth to interplanetary distances. Tracking and data-handling equipment to support these missions is provided. Present facilities permit simultaneous control of a newly launched spacecraft and a second one already in flight. In preparation for the increased number of U.S. activities in space, a capability is being developed for simultaneous control of either two newly launched spacecraft plus two in flight, or four spacecraft in flight. Advanced communications techniques are being implemented to make possible obtaining data from, and tracking spacecraft to, planets as far out in space as Jupiter.
NAVIGATION AND GUIDANCE↗
Entry capsule orbit determination accuracy
On-board tracking system of two-way coherent Doppler between entry capsule and orbiting bus for determining orbit of entry capsule and estimating atmospheric parameters.
COHERENT RADAR↗
Theoretical basis for the double precision orbit determination program. V - Doppler and range observables
Theoretical basis for double precision orbit determination program - formulation for computing two-way Doppler and round-trip range
SECOND↗
Doppler systems.
Doppler tracking systems as velocity measuring systems, including introduction methods for necessary position knowledge, one- and two-way systems analyses, etc
RANGE AND RANGE RATE TRACKING↗
Site survey for optimum location of Optical Communication Experimental Facility
Site survey was made to determine the optimum location for an Optical Communication Experimental Facility /OCEF/ and to recommend several sites, graded according to preference. A site was desired which could perform two-way laser communication with a spacecraft and laser tracking with a minimum of interruption by weather effects.
Source record↗
Elliptic Capture Orbits for Missions to the Near Planets
Elliptic capture orbits around Mars and Venus have often been considered as means for reducing arrival and departure energy requirements for two-way missions. It had also generally been feared that the energy savings obtained by capturing a spacecraft into a highly elliptical orbit (rather than a near circular orbit of the same periapsis) would largely be offset by the penalties incurred in aligning the semi-major axis of the ellipse in such a way as to obtain the proper orientation of the departure hyperbola. This paper, presents the results of an analysis which takes into consideration the penalties arising from the requirement to match the orientation of the elliptical orbit with the asymptote of the departure hyperbola. The scientific aspects of elliptical orbits around the target planet are discussed, and it is shown that such orbits exhibit characteristics which may be considered advantageous or disadvantageous depending on the purpose of the mission. Alignment of ' the semi-major axis of the capture, ellipse relative to the, asymptote of the escape hyperbola was found not to be a critical requirement since the kinetic energy remains high over a substantial portion of the elliptical capture orbit. This 'means that the escape stage can operate efficiently even when ignited at some angle from the true periapsis point. Considerable freedom in choosing this angle is available at little propulsive cost. The resulting latitude in the choice of angles between arrival and escape asymptotes makes it possible to consider a wide variety of interplanetary transfers and planetary staytimes without the need for separate propulsive maneuvers to realign the capture ellipse before departure., Special consideration has also been g1ven to plane change maneuvers around the planet. These may be required for reasons of orbit dynamics or scientific experimentation and are not uniquely tied to elliptical captures. The sensitivity of the mass of the excursion module to the eccentricity of the capture orbit is discussed and mass-penalty diagrams are presented. It is shown that these penalties do not materially offset the large gains obtained through the use of the elliptical capture mode.
Casal, Federico G.↗
Position Location and Aircraft Communication Equipment /PLACE/
Position location and communication equipment for two-way voice and signal data communication between aircraft and ground control facilities, using geosynchronous satellite transponders
Allen, W. K.↗
Block-coded communications
Theory for block-coded telemetry systems is useful in testing performance of one- and two-way, phase-coherent telemetry systems when double-conversion, superheterodyne, phase-locked receiver, preceded by bandpass limiter is used to track carrier.
Lindsey, W. C.↗
Astronaut Rescue Air Pack (ARAP) and Emergency Egress Air Pack (EEAP)
Two designs for a lightweight, low profile, mobile rescue apparatus providing a 15-minute air supply and self-contained two-way communications assembly are described. Units are designed for astronaut use in hazardous environments.
Barnhart, W. L.↗
Studies of nuclear light bulb start-up conditions and engine dynamics
Deep Space Network for two-way communications with unmanned spacecraft at planetary distances - Vol. 2
Bauer, H. E.↗
Laser communication experiment. Volume 1: Design study report: Spacecraft transceiver. Part 1: Transceiver design
The ATS-F Laser Communications Experiment (LCE) is the first significant step in the application of laser systems to space communications. The space-qualified laser communications system being developed in this experiment, and the data resulting from its successful deployment in space, will be applicable to the use of laser communications systems in a wide variety of manned as well as unmanned space missions, both near earth and in deep space. Particular future NASA missions which can benefit from this effort are the Tracking and Data Relay Satellite System and the Earth Resources Satellites. The LCE makes use of carbon dioxide lasers to establish simultaneous, two-way communication between the ATS-F synchronous satellite and a ground station. In addition, the LCE is designed to permit communication with a similar spacecraft transceiver proposed to be flown on ATS-G, nominally one year after the launch of ATS-F. This would be the first attempt to employ lasers for satellite-to-satellite communications.
Source record↗
Laser communication experiment. Volume 1: Design study report: Spacecraft transceiver. Part 3: LCE design specifications
The requirements for the design, fabrication, performance, and testing of a 10.6 micron optical heterodyne receiver subsystem for use in a laser communication system are presented. The receiver subsystem, as a part of the laser communication experiment operates in the ATS 6 satellite and in a transportable ground station establishing two-way laser communications between the spacecraft and the transportable ground station. The conditions under which environmental tests are conducted are reported.
Source record↗
Participation of Bell Telephone Laboratories in Project Echo and Experimental Results
On August 12, 1960, Echo I, a 100-foot-diameter spherical balloon, was placed in orbit around the earth by the National Aeronautics and Space Administration. The objective was to demonstrate the feasibility of long-distance communication by microwave reflection from a satellite. A two-way coast-to-coast voice circuit was to be established between the Jet Propulsion Laboratory (JPL) facility in California and a station provided by Bell Telephone Laboratories (STL) in New Jersey. Similar tests were also planned with the Naval Research Laboratory and other stations. This paper describes the general organization and operation of the Holmdel, New Jersey, station, and discusses the results of the experiments performed between the balloon launching and March 1, 1961. Successful voice communication was achieved through a variety of modulation methods including frequency modulation with feedback, amplitude modulation, single-sideband modulation, and narrow-band phase modulation. Careful measurements were also made of the loss in the transmission path.
Jakes, William C., Jr.↗