Engineering topics
Connolly, J.
Publications and source records attributed to Connolly, J..
Spacecraft Conceptual Design Compared to the Apollo Lunar Lander
Future human exploration of the Moon will require an optimized spacecraft design with each sub-system achieving the required minimum capability and maintaining high reliability. The objective of this study was to trade capability with reliability and minimize mass for the lunar lander spacecraft. The NASA parametric concept for a 3-person vehicle to the lunar surface with a 30% mass margin totaled was considerably heavier than the Apollo 15 Lunar Module "as flown" mass of 16.4 metric tons. The additional mass was attributed to mission requirements and system design choices that were made to meet the realities of modern spaceflight. The parametric tool used to size the current concept, Envision, accounts for primary and secondary mass requirements. For example, adding an astronaut increases the mass requirements for suits, water, food, oxygen, as well as, the increase in volume. The environmental control sub-systems becomes heavier with the increased requirements and more structure was needed to support the additional mass. There was also an increase in propellant usage. For comparison, an "Apollo-like" vehicle was created by removing these additional requirements. Utilizing the Envision parametric mass calculation tool and a quantitative reliability estimation tool designed by Valador Inc., it was determined that with today?s current technology a Lunar Module (LM) with Apollo capability could be built with less mass and similar reliability. The reliability of this new lander was compared to Apollo Lunar Module utilizing the same methodology, adjusting for mission timeline changes as well as component differences. Interestingly, the parametric concept's overall estimated risk for loss of mission (LOM) and loss of crew (LOC) did not significantly improve when compared to Apollo.
MarsLab: A HEDS Lander Concept
Recognizing that the human exploration of Mars will be a science-focused enterprise, the Human Exploration and Development of Space (HEDS) program set out three years ago to develop a mix of science and technology Lander payloads as a first step toward a human mission. With three experiments ready for flight and four more in development, the HEDS Mars program has the capability to stage missions with considerable impact. This presentation describes one such mission design by no means unique. Ambitious in scope, it encompasses elements of all seven HEDS payloads in a configuration with a uniquely HEDS character. Pragmatically, a subset of these elements could be selected for existing small Lander platforms. Bristling with scientific experiments, technology demonstrations, and outreach elements, MarsLab represents a prototype of a manned science station or scientific outpost. A cartoon overview of MarsLab defines its major elements, explained more fully in the sections that follow. The concept is endorsed by PI's of the various HEDS payloads, details of which are presented elsewhere at this workshop.
U.S. Biomedical Experiments In A Soviet Biosatellite
NASA technical memorandum contains final report on number of U.S. experiments, mainly biomedical experiments on rats, carried out aboard Soviet Biosatellite Cosmos 1887. Satellite launched on September 29, 1987, and recovered on October 12, 1987. More than 50 NASA-sponsored scientists from Ames Research Center and from universities throughout the United States involved directly in 26 U.S./U.S.S.R. experiments.
Efficient AlGaAs channeled-substrate-planar distributed feedback laser
A wavelength-locked, AlGaAs channeled-substrate-planar distributed feedback laser has been made that operates to 40 mW pulsed. The Bragg grating is situated at the shoulders of the layers of AlGaAs and GaAs. Overall power efficiencies of 15 percent have been measured at 40 mW of output power.