An Analysis of Errors in the Geographic Referencing of Nimbus Cloud Pictures |
From inside the book
Results 1-5 of 17
Page
... Pitch and Roll Attitude Control · Yaw Attitude Control · i 1 2 2 3 4 • 4 5 SOURCES OF ERROR IN THE ATTITUDE CONTROL SYSTEM . Input Signal Control System . Momentum , White Noise and Telemetry Scale . • ATTITUDE ERRORS FOR VARIOUS ...
... Pitch and Roll Attitude Control · Yaw Attitude Control · i 1 2 2 3 4 • 4 5 SOURCES OF ERROR IN THE ATTITUDE CONTROL SYSTEM . Input Signal Control System . Momentum , White Noise and Telemetry Scale . • ATTITUDE ERRORS FOR VARIOUS ...
Page 2
... errors . The yaw attitude is detected by an integrating rate gyro which gen- erates an error signal input to the yaw flywheel in the control system . See References 1 and 2 for a detailed discussion of the control system . Pitch and ...
... errors . The yaw attitude is detected by an integrating rate gyro which gen- erates an error signal input to the yaw flywheel in the control system . See References 1 and 2 for a detailed discussion of the control system . Pitch and ...
Page 3
... error . Pitch and roll errors are computed alternately and applied to a digital - to - analog converter which furnishes the proper error signal to the flywheels and pneumatics . Control Subsystem The pitch and roll attitude control ...
... error . Pitch and roll errors are computed alternately and applied to a digital - to - analog converter which furnishes the proper error signal to the flywheels and pneumatics . Control Subsystem The pitch and roll attitude control ...
Page 4
... pitch axis will result in a small , constant pitch error since the pitch momentum is not involved in the cyclic exchange mechanism . The max- imum attitude error due to this effect is estimated to be about one half a degree . SOURCES OF ...
... pitch axis will result in a small , constant pitch error since the pitch momentum is not involved in the cyclic exchange mechanism . The max- imum attitude error due to this effect is estimated to be about one half a degree . SOURCES OF ...
Page 5
... pitch and roll errors shown in Table 1a this 2 to 1 ratio has been applied in the manner which pro- duces the maximum error . Since yaw is under gyro control the above type of input signal error is not present . Control System This ...
... pitch and roll errors shown in Table 1a this 2 to 1 ratio has been applied in the manner which pro- duces the maximum error . Since yaw is under gyro control the above type of input signal error is not present . Control System This ...
Common terms and phrases
50 naut ANALYSIS OF ERRORS ANGLE FROM CENTER attitude control attitude error attitude from telemetered bolometer cause a maximum CENTER PICTURE PRINCIPAL cloud elements control system D-2137 National Aeronautics Darling data are expected determination of satellite earth error curve error due error is tolerable error of 50 error signal Eugene Figure B1 future Nimbus vehicles GEOGRAPHIC REFERENCING grid square GRIDDING ERROR naut gyro horizon attitude computer HRIR input signal error maximum gridding error maximum overall error mean cloud mean maximum gridding NASA TN NIMBUS CLOUD PICTURES orbital plane PICTURE PRINCIPAL POINT pitch and roll pitch axis pitch error PRINCIPAL POINT degrees projection plane REFERENCING OF NIMBUS right triangles roll and yaw roll error rotation satellite attitude scanner data Scanner Pulse Reconstruction scanner system side picture spherical triangle sun sensor Table 1a TECHNICAL NOTE D-2137 telemetered data TN D-2137 National total error TOTAL GRIDDING ERROR triangle R'P'A White Noise yaw error