Start Date
4-1969 8:00 AM
Description
The design, development, and flight test results of the Biosatellite attitude control system shall be discussed. Preliminary remarks describing the several Biosatellite missions shall show how mission constraints were interpreted by the controls engineer and how the "zero - gu and recovery requirements were ultimately translated into attitude control performance criteria. Results of analyses of payload perturbing effects shall answer questions of the nature: What are the forces and moments to which the payload is sensitive ? From what sources are these disturbances derived ? How can payload accelerations of the order of 10"~5 - g be sensed and controlled in a practical and economic way?
The paper shall also include a discussion on the prominent role a continuing simulation activity played in the development of the attitude control system. Of particular interest to the controls oriented engineer will be the discussion stressing the importance of these simulation studies to the analysis and evaluation of control system performance in the deorbit phase of the mission. Here, performance of state-of-the-art hardware will be evaluated and its selection justified. Also included in these remarks will be comments on the effects of geophysical phenomena on sensors and how these were incorporated in the simulation program to enhance its validity. Control system configuration shall be defined and features, such as the versatility of recovery time and location, will be discussed.
The Impact of Biosciences Requirements on Biosatellite Attitude Control
The design, development, and flight test results of the Biosatellite attitude control system shall be discussed. Preliminary remarks describing the several Biosatellite missions shall show how mission constraints were interpreted by the controls engineer and how the "zero - gu and recovery requirements were ultimately translated into attitude control performance criteria. Results of analyses of payload perturbing effects shall answer questions of the nature: What are the forces and moments to which the payload is sensitive ? From what sources are these disturbances derived ? How can payload accelerations of the order of 10"~5 - g be sensed and controlled in a practical and economic way?
The paper shall also include a discussion on the prominent role a continuing simulation activity played in the development of the attitude control system. Of particular interest to the controls oriented engineer will be the discussion stressing the importance of these simulation studies to the analysis and evaluation of control system performance in the deorbit phase of the mission. Here, performance of state-of-the-art hardware will be evaluated and its selection justified. Also included in these remarks will be comments on the effects of geophysical phenomena on sensors and how these were incorporated in the simulation program to enhance its validity. Control system configuration shall be defined and features, such as the versatility of recovery time and location, will be discussed.
Comments
No other information or file available for this session.