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  1. IEEE Transactions on Aerospace and Navigational Electronics
  2. Year : 1963 Volume : ANE-10
  3. Issue 1
  4. Digital Attitude Control System
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Year : 1965 Volume : 12
Year : 1964 Volume : ANE-11
Year : 1963 Volume : ANE-10
Issue 4
Issue 3
Issue 2
Issue 1
IEEE Transactions on Aerospace and Navigational Electronics
IEEE Professional Technical Group on Aerospace and Navigational Electronics
An Accuracy Study of a Doppler Navigation System Assuming Time-Stationary Random Input Errors
Optimal Levelling and Gyrocompassing of Inertial Systems
A Diplex, Doppler Phase Comparison Radar
Antenna Squint and Guidance Errors
A DME Based on Standing Wave Conditions
Digital Attitude Control System
Null-Tracking Doppler-Navigation Radar
A Sum-and-Difference Interferometer System for HF Radio Direction Finding
Field-of-Interest Survey
Abtstracts
Book Reviews
PTGANE News
Contributors
Suggestions to authors
Institutional listings
Year : 1963 Volume : Technical_Paper

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Digital Attitude Control System

Content Provider IEEE Xplore Digital Library
Author Carney, R. Conover, T.
Copyright Year 1963
Abstract A simple ¿minimum-fuel,¿ digital attitude control system requiring no rate gyros is described; the system is applicable to practically any type of orbiting space vehicle. An inertial guidance computer furnishes a quantized attitude angle to the control system. With this attitude information and a measure of time, the control computer accurately computes the vehicle's average rate. A novel switching zone arrangement in the phase plane results in decisions controlling on-off reaction jets that adjust the vehicle's attitude. Jet selection and duration of the jets' operation are determined as a function of the vehicle's angular position and average rate in relation to the switching zones in the phase plane. The system operates so that computed rates are very accurate when accurate rates are required and less accurate when accuracy is not important. The end result is a system that converges to a low-rate limit cycle while consuming near-minimum fuel. The parameters controlling the switching logic are prestored memory constants which are electronically loadable and changeable. This flexibility makes the system compatible with a wide variety of payloads and missions.
Starting Page 45
Ending Page 49
Page Count 5
File Size 824507
File Format PDF
ISSN 00961957
Volume Number ANE-10
Issue Number 1
Language English
Publisher Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Publisher Date 1963-03-01
Access Restriction Subscribed
Rights Holder Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Subject Keyword Attitude control Space vehicles Navigation Control systems Extraterrestrial measurements Time measurement Limit-cycles Fuels Logic Payloads
Content Type Text
Resource Type Article
Subject Electrical and Electronic Engineering Aerospace Engineering
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