On the use of Euler's theorem on rotations for the synthesis of attitude control systems
Euler theorem applied to rotations for synthesis of attitude control systems
SEARCH · Search NASA
Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.
Euler theorem applied to rotations for synthesis of attitude control systems
Attitude control system for advanced orbiting solar observatory /aoso/, with attention to means of obtaining increased reliability
Design of the attitude control system for the orbiting geophysical observatory, discussing control laws, sensors, torque sources, reaction wheel system and pneumatic system
Performance test data for ammonia resistojet attitude control system of stable platform satellites
Minimum sensitivity design of attitude control systems for spacecraft
Development of attitude control system for sounding rocket stabilization during ballistic phase of flight
Optimized momentum and attitude control system /MACS/ for Skylab class space stations employing control moment gyro and reaction jet elements
Feasibility of common stage for alternate space missions and attitude control systems for unmanned spacecraft propulsion system
Air bearing platform simulators for testing space vehicle attitude control systems
Design, operation and performance of mariner ii attitude control system used to carry out mission to venus
Automatic attitude control system test for satellite using inertia wheels mounted on air bearings
In this paper, the details of the design, construction and performance of the attitude control system are presented. The attitude control system has been used to meet certain SIM requirements. An example of this performance test is also included.
Complete computer simulation and equilibrium analysis of spacecraft attitude control systems
Gyromagnetic attitude control system for meteorological satellite
An Integrated Power and Attitude Control System (IPACS) concept with potential application to a broad class of space missions is discussed. A description is given of the basic concept of combining the onboard energy storage and attitude control functions by storing energy in spinning flywheels which are used to provide control torques. A shuttle-launched Research and Applications Module (RAM) A303B solar-observatory mission having stringent pointing requirements (1.0 arc second) is selected to investigate possible interactions between energy storage and attitude control. A simulation of this spacecraft involving actual laboratory-model control-system hardware is presented. Simulation results are discussed which indicate that the IPACS concept, even in a failure-mode configuration, can readily meet the RAM A303B pointing requirements.
Design technology of attitude control systems for large launch vehicles
Translational forces on Mariner 5 stemming from attitude control system studied to determine trajectory for scientific and operational purposes
Translational forces on Mariner 5 stemming from attitude control system, determining trajectory for scientific and operational purposes