Aerospace systems and mission analysis research Status report, 1 Apr. - 31 Dec. 1966
Systems and mission analysis of solar electric propulsion for solar system exploration
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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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Systems and mission analysis of solar electric propulsion for solar system exploration
System reliability improvements based on design and reliability experience producing increased success percentage of NASA systems from 62 to 87 percent
Human water consumption and output as function of space type diets and simulated space environmental conditions to assess water balance
Mission analysis for solar electric propelled spacecraft on Mars Orbiter, Jupiter flyby, and asteroid belt exploration trajectories
Characteristics of shock loads on spacecraft structures produced by pyrotechnics and explosive devices - Vol. 1
Pyrotechnic shock data associated with structure cutting charges consisting of mild detonating fuse and flexible linear shaped charge - Vol. 2
Determination of shock loads on spacecraft structures created by explosive separation of components - Vol. 3
Compilation of shock loads on spacecraft structures produced by actuation of pyrotechnics and explosive devices - Vol. 4
Characteristics of shock loads induced on spacecraft structures by initiation of explosive pin pullers - Vol. 5
Design of structures and equipment to reduce shock loads induced by pyrotechnics and explosive devices - Vol. 6
Airborne remote sensing application to agriculture and forestry for crop forecasting, soil mapping, insect infestation detection and range surveys
Principle comprises primary cost impacts, such as operational delays, reflown missions due to aborts, procurement of equipment, and vehicle expansion to accommodate additional equipment. Economics are estimated by criterion which is relatively insensitive to impertinent cost factors.
This AGARD graph addresses the advances effected in the theory and design of modern optimal guidance and control systems, in the following areas: Part I: Theory, Part II: Design Techniques, Part III: Applications and should provide an aid in the application of these modern techniques. This AGARD graph was prepared at the request of the Guidance and Control Panel of AGARD.
NASA has recently established a maintainability and maintenance planning program. This paper presents an overview of the program and discusses the specific application of the maintainability requirements as contained in NASA handbook (NHB) 5300.4 (1E), 'Maintainability Program Requirements for Space Systems'. Suggestions regarding the extent to which these requirements should be applied during each phase of program development also are presented.
The goal is to develop the next generation guidance and control analysis and design tools to enable future missions and to improve productivity and reliability.
The proceedings of the workshop are presented. Some areas of discussion are as follows: modeling, systems identification, and control of flexible aircraft, spacecraft, and robotic systems.
The concept of damage-mitigating control is to minimize fatigue (as well as creep and corrosion) damage of critical components of mechanical structures while simultaneously maximizing the system dynamic performance. Given a dynamic model of the plant and the specifications for performance and stability robustness, the task is to synthesize a control law that would meet the system requirements and, at the same time, satisfy the constraints that are imposed by the material and structural properties of the critical components. The authors present the concept of damage-mitigating control systems design with the following objectives: (1) to achieve high performance with a prolonged life span; and (2) to systematically update the controller as the new technology of advanced materials evolves. The major challenge is to extract the information from the material properties and then utilize this information in a mathematical form so that it can be directly applied to robust control synthesis for mechanical systems. The basic concept of damage-mitigating control is illustrated using a relatively simplified model of a space shuttle main engine.
Although significant advances have been made in modeling and controlling flexible systems, there remains a need for improvements in model accuracy and in control performance. The finite element models of flexible systems are unduly complex and are almost intractable to optimum parameter estimation for refinement using experimental data. Distributed parameter or continuum modeling offers some advantages and some challenges in both modeling and control. Continuum models often result in a significantly reduced number of model parameters, thereby enabling optimum parameter estimation. The dynamic equations of motion of continuum models provide the advantage of allowing the embedding of the control system dynamics, thus forming a complete set of system dynamics. There is also increased insight provided by the continuum model approach.