Start Date
4-1968 8:00 AM
Description
This paper establishes design criteria for a fluidic attitude control system for a solar probe. Results of an analytical and experimental investigation are presented to indicate that fluidic control is both possible and practical.
A system is designed to meet the control system requirements. A block diagram of the control system is discussed and derivations of the transfer functions explained. The system response is determined for the radii of 1 AU maximum and 0.3 AU minimum.
System performance is described and computer solutions for the vehicle's attitude response obtained. Performance is discussed in terms of two separate modes of operation: a short-term mode (hundreds of seconds) and a long-term mode (thousands of seconds). As a result of this system analysis, an important parameter, called the "normalized system gain,' 1 appears. This parameter is useful in scaling the spacecraft in order to design the short term response of the simulator.
Problems associated with simulator fabrication and performance are discussed and experimental data on its performance presented. Fabrication of the components, components characteristics, and component integration are also discussed.
Fluidic Attitude Control System — Solar Probe
This paper establishes design criteria for a fluidic attitude control system for a solar probe. Results of an analytical and experimental investigation are presented to indicate that fluidic control is both possible and practical.
A system is designed to meet the control system requirements. A block diagram of the control system is discussed and derivations of the transfer functions explained. The system response is determined for the radii of 1 AU maximum and 0.3 AU minimum.
System performance is described and computer solutions for the vehicle's attitude response obtained. Performance is discussed in terms of two separate modes of operation: a short-term mode (hundreds of seconds) and a long-term mode (thousands of seconds). As a result of this system analysis, an important parameter, called the "normalized system gain,' 1 appears. This parameter is useful in scaling the spacecraft in order to design the short term response of the simulator.
Problems associated with simulator fabrication and performance are discussed and experimental data on its performance presented. Fabrication of the components, components characteristics, and component integration are also discussed.
Comments
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