Single-Axis Attitude Regulation of Extra-Atmospheric Vehicles

Item

Title
Single-Axis Attitude Regulation of Extra-Atmospheric Vehicles
Description
Three-degree-of-freedom rotational equations of motion characterizing an extra-atmospheric vehicle are simplified for single axis motions only. Linear analyses are made in which the simplified vehicle motions are controlled by a variety of automatic control systems using inertial wheels and/or mass ejection. Nonlinear control of the same vehicle is then considered using phase plane analysis. Equalization and several types of realistic nonlinearities are considered, and such quantities as maximum attitude, attitude rate, and power expended during a corrective maneuver are determined. The effects of controller type, i.e., inertial wheel or mass ejection, equalization, and various nonlinearities upon limit cycle behavior and upon impulse expended in a limit cycle condition are developed in literal terms, and a summary is given. The analysis evolves from simple to more complex and realistic cases so as to illustrate methods and concepts which can be used at a preliminary design level. Examples are given of tradeoffs illustrating how the controller-vehicle may be optimized with respect to one or more dynamic requirements, such as speed of response, impulse expenditure, and accuracy.
Date
1962
Index Abstract
Contrails only
Photo Quality
Not Needed
Report Number
ASD TR 61-129
Creator
Peters, R. A.
Kovacevich, V. J.
Graham, Dunstan
Corporate Author
Systems Technology, Inc.
Laboratory
Flight Control Laboratory
Extent
238
Identifier
AD0277221
AD0277221
Access Rights
OTS
Distribution Classification
1
Contract
AF 33(616)-5961
DoD Project
8219
DoD Task
82162
DTIC Record Exists
Yes
Distribution Change Authority Correspondence
None
Report Availability
Full text available by request
Date Issued
1962-02
Abstract
Three-degree-of-freedom rotational equations of motion characterizing an extra-atmospheric vehicle are simplified for single axis motions only. Linear analyses are made in which the simplified vehicle motions are controlled by a variety of automatic control systems using inertial wheels and/or mass ejection. Nonlinear control of the same vehicle is then considered using phase plane analysis. Equalization and several types of realistic nonlinearities are considered, and such quantities as maximum attitude, attitude rate, and power expended during a corrective maneuver are determined. The effects of controller type, i.e., inertial wheel or mass ejection, equalization, and various nonlinearities upon limit cycle behavior and upon impulse expended in a limit cycle condition are developed in literal terms, and a summary is given. The analysis evolves from simple to more complex and realistic cases so as to illustrate methods and concepts which can be used at a preliminary design level. Examples are given of tradeoffs illustrating how the controller-vehicle may be optimized with respect to one or more dynamic requirements, such as speed of response, impulse expenditure, and accuracy.
Provenance
AFRL/VACA
Type
report
Subject
Space Flight
Attitude Control Systems
Gyro Stabilizers
Jet Flow
Mathematical Analysis
Roll
Artificial Satellites
Servomechanisms
Spacecraft
Stabilization Systems
Tables (Data)
Torque
Publisher
Wright-Patterson Air Force Base, OH : Flight Control Laboratory, Aeronautical Systems Division, Air Force Systems Command
Format
xviii, 238 pages : ill.; 28 cm.
Distribution Conflict
No