Satellite Power Systems (SPS) Space Transportation Workshop Summary

Space transportation requirements are major elements in the technical and economic realization of the entire SPS concept. First, steps in enhancing the shuttle include the Titan based liquid boost module (LBM) and liquid propellant boosters (LPB) to replace the present solid rocket boosters (SRB). The next choice between new ballistic or winged boosters must still be made; as well as the choice between series (staged) and parallel operation. Entirely new vehicles of large size are required before the economic and environmental problems of the prototype, or even demonstration, SPS can be resolved. Social impacts such as noise, and atmospheric pollution, locally and in the ionosphere, must be fully addressed. Although rather advanced technology and well developed operational management is required to properly target the average cost of gross cargo payloads into LEO at 30 $(1979)/kg for the construction of the initial SPS, the further goal for repetitive construction of 30 to 60 SPS at 15$ (1979)/kg for all operational payloads require the use of very advanced, long lived vehicles with a sophisticated operational organization using off shore, equatorial launch sites

Jp24 transient pressure measuring methods research status report, 1 jan. - 31 mar. 1965

Transient pressure transducer evaluation and improvement of laboratory electric equipment and technique

Comments on dual-mode nuclear space power and propulsion system concepts

Some form of Dual-Mode Nuclear Space Power & Propulsion System (D-MNSP&PS) will be essential to spacefaring throughout teh solar system and that such systems must evolve as mankind moves into outer space. The initial D-MNPSP&PS Reference System should be based on (1) present (1990), and (2) advanced (1995) technology for use on comparable mission in the 2000 and 2005 time period respectively. D-MNSP&PS can be broken down into a number of subsystems: Nuclear subsystems including the energy source and controls for the release of thermal power at elevated temperatures; power conversion subsystems; waste heat rejection subsystems; and control and safety subsystems. These systems are briefly detailed

Solar electric space mission analysis Progress report, 1 Jun. - 31 Dec. 1966

Characteristics and trajectory analysis of solar electric propulsion space missions - Mars orbiter and Jupiter flyb

Aerospace systems and mission analysis research Status report, 1 Apr. - 31 Dec. 1966

Systems and mission analysis of solar electric propulsion for solar system exploratio

Enroute flight planning: The design of cooperative planning systems

Design concepts and principles to guide in the building of cooperative problem solving systems are being developed and evaluated. In particular, the design of cooperative systems for enroute flight planning is being studied. The investigation involves a three stage process, modeling human performance in existing environments, building cognitive artifacts, and studying the performance of people working in collaboration with these artifacts. The most significant design concepts and principles identified thus far are the principle focus

Aerospace systems and mission analysis research - Solar electric space mission analysis Final report

Mission analysis for solar electric propelled spacecraft on Mars Orbiter, Jupiter flyby, and asteroid belt exploration trajectorie

Finite element methods for first order systems with applications to mixed equations (Mathematical Sciences)

Issued as Annual progress report and Final report, Project no. G-37-63