The IUS TVC SERVO SYSTEM which consists of four electrically redundant electromechanical actuators, four potentiometer assemblies, and two controllers to provide movable nozzle control on both IUS solid rocket motors is developed. An overview of the more severe IUS TVC servo system design requirements, the system and component designs, and test data acquired on a preliminary development unit is presented. Attention is focused on the unique methods of sensing movable nozzle position and providing for redundant position locks
The paper describes the initial results of a research activity aimed at developing a high integrity ...
The thrust vector control (TVC) system of the Viking Orbiter 1975 is discussed. The purpose of the T...
Two controllers are developed to provide attitude control of a spinning rocket that has a thrust vec...
At present, actuation systems for the Thrust Vector Control (TVC) for launch vehicles are hydraulic ...
The objective of this research was to develop control schemes and control design procedures for elec...
A design method for a servo compensator is developed in the frequency domain using singular values. ...
Reliability analyses and failure probabilities of S-4B stage automatic pilots and hydraulic thrust v...
An electromechanical actuator was developed that will follow a proportional control command with min...
When a rocket is launched, there is a short initial period of acceleration during which the rocket i...
Hydraulic actuators are currently used to operate the propellant control valves (PCV) for the space ...
Design of electric motors which fulfill the needs of Thrust Vector Control (TVC) actuators used in l...
This paper introduces a model-based Fault Detection and Isolation (FDI) approach for a Reusable Laun...
A description of a mathematical model reference system is presented which provides redundancy manage...
Proportional-pressure control servovalve consisting of fluid amplifier bellows-driven jet-pipe and t...
University of Würzburg, Informatics VIII aims in developing a rocket simulator test bed in aspect of...
The paper describes the initial results of a research activity aimed at developing a high integrity ...
The thrust vector control (TVC) system of the Viking Orbiter 1975 is discussed. The purpose of the T...
Two controllers are developed to provide attitude control of a spinning rocket that has a thrust vec...
At present, actuation systems for the Thrust Vector Control (TVC) for launch vehicles are hydraulic ...
The objective of this research was to develop control schemes and control design procedures for elec...
A design method for a servo compensator is developed in the frequency domain using singular values. ...
Reliability analyses and failure probabilities of S-4B stage automatic pilots and hydraulic thrust v...
An electromechanical actuator was developed that will follow a proportional control command with min...
When a rocket is launched, there is a short initial period of acceleration during which the rocket i...
Hydraulic actuators are currently used to operate the propellant control valves (PCV) for the space ...
Design of electric motors which fulfill the needs of Thrust Vector Control (TVC) actuators used in l...
This paper introduces a model-based Fault Detection and Isolation (FDI) approach for a Reusable Laun...
A description of a mathematical model reference system is presented which provides redundancy manage...
Proportional-pressure control servovalve consisting of fluid amplifier bellows-driven jet-pipe and t...
University of Würzburg, Informatics VIII aims in developing a rocket simulator test bed in aspect of...
The paper describes the initial results of a research activity aimed at developing a high integrity ...
The thrust vector control (TVC) system of the Viking Orbiter 1975 is discussed. The purpose of the T...
Two controllers are developed to provide attitude control of a spinning rocket that has a thrust vec...