Conceptual design studies of an advanced Mariner spacecraft. Volume I - Summary
Parametric analysis and conceptual design study summary for advanced Mariner space probe - flyby bus and lander configuration for Mars investigation
LANDING SYSTEM↗
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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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Thermal scale modeling of the temperature control model of Mariner Mars 64, phase II
Equilibrium temperature testing on thermal scale model of Mariner Mars 64 spacecraft bus
MARS SPACECRAFT↗
Addressable time division data system
Design considerations of central programmer, common address, and data return bus
TELEMETRY↗
Voyager capsule phase B. Volume I - Summary Final report
Mission objectives, design criteria, and design constraints for preferred capsule bus concept of Voyager flight capsule
SPACE CAPSULE↗
Voyager capsule, preliminary design, phase B. Volume III - Surface laboratory system. Section II - Preliminary design for OSE FINAL report
Operational support equipment and mission dependent equipment for preliminary design of surface laboratory portion of Voyager capsule bus system
PLANETARY SURFACE↗
Voyager capsule, preliminary design, phase B. Volume IV - Entry science package. Section V - Interfaces Final report
Hardware, software, and service interfaces between capsule bus, entry science package, and Voyager spacecraft
SPACE CAPSULE↗
Voyager capsule, preliminary design, phase B. Volume V - Interface descriptions Final report
Hardware, software, and service interfaces between capsule bus, entry science package, surface laboratory, and Voyager spacecraft
VOYAGER PROJECT↗
RTG spacecraft study, volume 2 Final report
Design and implementation of radioisotope thermoelectric generators providing electric power to Voyager spacecraft bus
Kriprih, A.↗
Voyager capsule engine system design considerations single versus multiple engine configuration
Single versus multiple engine configurations for Voyager capsule bus propulsion
Source record↗
Interplanetary trajectory selection criteria for Voyager Mars missions.
Trajectory design criteria for Voyager Mars missions toward standardization of launch vehicle, shroud, spacecraft bus, capsule and propulsion systems
Stavro, W.↗
Parameters for good welding of copper to nickel
Quality in welding copper leads to nickel bus wires is obtained by the mass of nickel exceeding that of copper. Welding range 2ncreases proportionately with the increase in the nickel-to-copper mass ratio up to 4-to-1.
Hall, L. G.↗
The IMP-F and G preboost regulator
Preboost main bus regulator for IMP satellite power system
Rodriguez, G. E.↗
A survey of digital baseband signaling techniques
Survey of digital baseband signaling techniques for space shuttle data bus
Deffebach, H. L.↗
Development and performance of pulse-width-modulated static inverter and converter modules
Pulse-width-modulated inverter and converter modules are being developed for modular aerospace electrical power systems. The modules, rate 2.5 kilowatts per module and 10-minute - 150-percent overload, operate from 56 volts dc. The converter module provides two output voltages: a nominal link voltage of 200 volts dc when used with the inverter, and 150 volts dc to a load bus when used separately. The inverter module output is 400-hertz, sinusoidal, three-phase, 120/208 volts. Tests of breadboard models with standard parts and integrated circuits show rated power efficiencies of 71.4 and 85.1 percent and voltage regulation of 5 and 3.1 percent for inverter and converter modules, respectively. Sine-wave output distortion is 0.74 percent.
Pittman, P. F.↗
A stored program channel processor for CAMAC
A PDP-15 interface was developed for the CAMAC instrumentation standard which implements the features of both the addressable I/0 bus and the single cycle data channel. The data channel section forms an independent I/0 processor which executes programs stored in core. Programs consist of CAMAC commands plus special control characters and commands.
Bercaw, R. W.↗
Crew/cargo and logistics module definition
The logistics requirements for the space station cargo, the initial buildup, and the 90 day resupply are presented, along with the conceptual selection for the orbiter crew accommodations and the GSS logistics system. Various module configurations are outlined; structural/mechanical, environmental, temperature, voice communication, and data bus subsystems are also reviewed. Ground operations and module prelaunch and launch operations are discussed, as well as logistics system interfaces for space shuttles and stations.
Source record↗
An On Board Processor (OBP) for OAO C
A stored program computer and its application on OAO is considered. The parallel computer has a memory capacity of 16,384 words of 18 bits each, one central processor unit, two 4096 word memory units, and one input/output unit. The I/O has no direct data connection with the CPU so that all data flow between these two units must pass through memory by way of the memory data bus. The primary functions of the onboard computer are auxiliary command storage, spacecraft monitoring and malfunction reporting, data compression and status summary, and possible performance of emergency corrective action.
Hartenstein, R. G.↗
Power conditioning equipment for a thermoelectric outer planet spacecraft, volume 1, book 1
Equipment was designed to receive power from a radioisotope thermoelectric generator source, condition, distribute, and control this power for the spacecraft loads. The TOPS mission, aimed at a representative tour of the outer planets, would operate for an estimated 12 year period. Unique design characteristics required for the power conditioning equipment results from the long mission time and the need for autonomous on-board operations due to large communications distances and the associated time delays of ground initiated actions. The salient features of the selected power subsystem configuration are: (1) The PCE regulates the power from the radioisotope thermoelectric generator power source at 30 vdc by means of a quad-redundant shunt regulator; (2) 30 vdc power is used by certain loads, but is more generally inverted and distributed as square-wave ac power; (3) a protected bus is used to assure that power is always available to the control computer subsystem to permit corrective action to be initiated in response to fault conditions; and (4) various levels of redundancy are employed to provide high subsystem reliability.
Andrews, R. E.↗