Optimum preemphasis-deemphasis filter characteristics for LCRU television
Optimum preemphasis-deemphasis filter pair for FM transmission of Lunar Communications Relay Unit color television
Pannelton, R. J.↗
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Apollo 15 Mission Report
A detailed discussion is presented of the Apollo 15 mission, which conducted exploration of the moon over longer periods, greater ranges, and with more instruments of scientific data acquisition than previous missions. The topics include trajectory, lunar surface science, inflight science and photography, command and service module performance, lunar module performance, lunar surface operational equipment, pilot's report, biomedical evaluation, mission support performance, assessment of mission objectives, launch phase summary, anomaly summary, and vehicle and equipment descriptions. The capability of transporting larger payloads and extending time on the moon were demonstrated. The ground-controlled TV camera allowed greater real-time participation by earth-bound personnel. The crew operated more as scientists and relied more on ground support team for systems monitoring. The modified pressure garment and portable life support system provided better mobility and extended EVA time. The lunar roving vehicle and the lunar communications relay unit were also demonstrated.
Source record↗
Roles of the ground and flight crew in Apollo operations.
The functions performed by ground personnel and flight crews of Apollo missions are reviewed, covering vehicle systems operation and management, Saturn launch vehicle, command-service and lunar modules, lunar rover, communication relay unit and ground-commanded TV assembly. Details of the flight path, scientific experiments, photographic equipment and crew health monitoring are also discussed in terms of these functions. The coordinated combination of large numbers of experts and data processing equipment on the ground with the crew's capabilities to operate the spacecraft and exercise on-the-spot judgements is viewed as the backbone of the successful fulfillment of Apollo missions.
Wolfer, B. M.↗
Coded communication link for an advanced manned spacecraft.
An analysis, in terms of key design parameters, is presented of a digital link for bidirectional communication between an advanced manned spacecraft, such as the space shuttle, and a ground terminal by means of a synchronous communication relay satellite. Performance of both ground to manned spacecraft and return links are compared with and without coding. A breadboard terminal for simulating the two-way link is described. Results of error rate tests are discussed.
Gould, L. M.↗
Pioneer spacecraft for atmospheric entry missions to the outer planets.
The composition of the atmospheres of the Jovian planets is probably representative of the composition of the original matter from which the solar system was formed. An entry probe would be required for obtaining quantitative data about the atmosphere as a function of altitude. A mission involving the detachment of an atmospheric entry probe from a Pioneer spacecraft is being considered. Instruments in the probe are to measure pressure, temperature, and composition of the atmosphere during descent. The Pioneer spacecraft is to serve as a communications relay for the data transmitted from the probe.
Dixon, W. J.↗
The role of satellites in snow and ice measurements
Earth-orbiting polar satellites are desirable platforms for the remote sensing of snow and ice. Geostationary satellites at a very high altitude (35,900 km) are also desirable platforms for many remote sensors, for communications relay, for flood warning systems, and for telemetry of data from unattended instrumentation in remote, inaccessible places such as the Arctic, Antarctic, or mountain tops. Optimum use of satellite platforms is achieved only after careful consideration of the temporal, spatial, and spectral requirements of the environmental mission. The National Environmental Satellite Service will maintain both types of environmental satellites as part of its mission.
Wiesnet, D. R.↗
Viking Mars launch set for August 11
The 1975-1976 Viking Mars Mission is described in detail, from launch phase through landing and communications relay phase. The mission's scientific goals are outlined and the various Martian investigations are discussed. These investigations include: geological photomapping and seismology; high-resolution, stereoscopic horizon scanning; water vapor and thermal mapping; entry science; meteorology; atmospheric composition and atmospheric density; and, search for biological products. The configurations of the Titan 3/Centaur combined launch vehicles, the Viking orbiters, and the Viking landers are described; their subsystems and performance characteristics are discussed. Preflight operations, launch window, mission control, and the deep space tracking network are also presented.
Panagakos, N.↗
An all-digital Manchester symbol synchronizer for Space Shuttle
The Shuttle S-Band relay communications links via TDRS are coded and may operate at symbol signal-to-noise ratios (Es/No) as low as -5dB. A brass-board all-digital bit synchronizer with very low (0.05dB) degradation relative to an idealized analog model has been designed to process the 216 KBPS Manchester data symbols. This all-digital bit synchronizer, which provides soft decision detected outputs to a convolutional decoder, may be operated at any rate below 216 KBPS by merely changing the master clock frequency.
Batson, B. H.↗
Pioneer Jupiter Orbiter/Probe mission. I - Spacecraft system description
This paper discusses the Pioneer Jupiter Orbiter/Probe mission with emphasis on the orbiter spacecraft system. In this mission, the atmosphere of Jupiter will be investigated for physical and chemical structure by a probe which survives entry and transmits data while descending below the 10-bar level. The spacecraft deflects after probe separation to a nonimpacting approach trajectory, acts as a communications relay for data from the descending probe, and propulsively enters an orbit about Jupiter. As an orbiter, it explores the environment of Jupiter for three years, making in situ measurements of the particles and fields of the Jovian magnetosphere together with remote measurements (including images) of Jupiter and the Galilean satellites. The spacecraft system is logically based on the design of Pioneers 10 and 11 with modifications for these different mission requirements: antenna, receiver, and memory for the probe-spacecraft data link; a retropropulsion system for the high velocity-change requirements of orbit insertion; a data system consistent with the requirements of a line-scan imaging system; and an improved complement of radioisotope-thermoelectric-generator power sources to provide adequate power six years after launch.
Lassen, H. A.↗
Special problems and capabilities of high altitude lighter than air vehicles
Powered LTA vehicles have historically been limited to operations at low altitudes. Conditions exist which may enable a remotely piloted unit to be operated at an altitude near 70,000 feet. Such systems will be launched like high altitude balloons, operate like nonrigid airships, and have mission capabilities comparable to a low altitude stationary satellite. The limited lift available and the stratospheric environment impose special requirements on power systems, hull materials and payloads. Potential nonmilitary uses of the vehicle include communications relay, environmental monitoring and ship traffic control.
Wessel, P. R.↗
Space construction engineering - A new career field
Opportunities for engineers in the design and construction of future large space structures are outlined. Possible space structures for the 1980's include a large mirror to reflect sunlight to earth for night lighting, an antenna for a personal communications system, a deep space communications relay system and a large passive radiometer to measure soil moisture. Considerations in the design of such structures include the lack of gravity, allowing structures to be built with much less supporting weight, the cost of transportation to orbit, leading to the use of aluminum or composite materials stored on reels and attached to a beam builder, and the required surface accuracy in the presence of thermal stresses. Construction factors to consider include the use of astronauts and remote manipulators in assembly, both of which have been demonstrated to be feasible.
Hagler, T.↗
Applications of a high-altitude powered platform /HAPP/
The high-altitude powered platform (HAPP) is a conceptual unmanned vehicle which could be either an airship or airplane. It would keep station at an altitude of 70,000 ft above a fixed point on the ground. A microwave power transmission system would beam energy from the ground up to the HAPP to power an electric motor-driven propeller and the payload. A study of the HAPP has shown that it could potentially be a cost-competitive platform for such remote sensing applications as forest fire detection, Great Lakes ice monitoring and Coast Guard law enforcement. It also has significant potential as a communications relay platform for (among other things) direct broadcast to home TVs over a large region.
Kuhner, M. B.↗
Data acquisition and projected applications of the observations from LANDSAT-D
The capabilities of the multispectral scanner and thematic mapper aboard LANDSAT-D are reviewed in terms of spectral, spatial, and radiometric resolution. The applications made possible by increased sensor sensitivity are discussed. Communication relay systems and the ground segment are also described.
Williams, D. L.↗
Aeroelastic considerations for continuous patrol/high altitude surveillance platforms
For the last several years, an investigation has been conducted regarding the feasibility of unmanned, airborne, High-Altitude Powered Platforms (HAPP), and High Surveillance Platforms for Over-the-Horizon Targeting (HI-SPOT). These airborne platforms have been proposed as a means of achieving a continuous regional communication-relay or for continuous regional surveillance for use in agricultural research or military applications, i.e., fleet support. These platforms would offer improvements over existing orbiting satellites. These improvements are related to better resolution and increased mission flexibility. The required mission endurance up to six months, would be obtained through the use of either solar power, a cryogenically fueled engine, or microwave-power. Attention is given to airborne platform configuration, structure, structural and aerodynamic modeling, modal analysis, and flutter analysis.
Turner, C. D.↗
Design study for remotely piloted, high-altitude airplanes powered by microwave energy
A design study has been conducted for unmanned, microwave-powered airplanes that must fly with long endurance at high altitude. They are proposed to conduct communications-relay, observation, or various scientific missions above approximately 55,000 feet altitude. The special characteristics of the microwave-power system and high-altitude, low-speed vehicle are reviewed. Examples of both sizing and performance analysis are used to suggest design procedure guidelines.
Morris, C. E. K., Jr.↗
Geosynchronous orbiter tracking by VLBI - Demonstration results
Results are presented on two experiments which were designed to demonstrate the feasibility of tracking geosynchronous satellites to an accuracy of 5 meters using Very-Long-Baseline Interferometry (VLBI). A communications relay satellite located over the mid-Pacific was observed using baselines between California, Australia and Guam Island. Differential VLBI observations between the satellite and angularly nearby extragalactic radio sources were used to measure the position of the satellite in the plane of the sky. Post-fit residuals to the adjusted trajectory were obtained which correspond to less than 10 meters in one dimension of the satellite position.
Donivan, F. F., Jr.↗
Tracking and Data Relay Satellite System (TDRSS)
The DSN (Deep Space Network) mission support requirements for the Tracking and Data Relay Satellite System (TDRSS) are summarized. The TDRSS consists of four identical satellites in geosynchronous orbits (35,800 km) and a dedicated ground station. The payload of each satellite is a telecommunications service system that relays communication signals between low earth-orbiting user spacecraft and the TDRSS ground terminal. Mission objectives are outlined and the DSN support requirements are defined through the presentation of tables and narratives describing the spacecraft flight profile; DSN support coverage; frequency assignments; support parameters for telemetry, command and support systems; and tracking support responsibility.
Mckenzie, J.↗
Microwave systems applications in deep space telecommunications and navigation - Space Exploration Initiative architectures
The general support requirements of a typical SEI mission set, along with the mission operations objectives and related telecommunications, navigation, and information management (TNIM) support infrastructure options are described. Responsive system architectures and designs are proposed, including a Mars orbiting communications relay satellite system and a Mars-centered navigation capability for servicing all Mars missions. With the TNIM architecture as a basis, key elements of the microwave link design are proposed. The needed new technologies which enable these designs are identified, and current maturity is assessed.
Hall, Justin R.↗