COMMAND SYSTEMS DEPARTMENT CRT OSCILLOSCOPE DISPLAY

1963 ◽  
Author(s):  
C. F. Wills
Keyword(s):  
Oscilloscope Display ◽  
Command Systems

Synthesizing safe control-command systems out of reusable components

2015 ◽  
Vol 44 ◽  
pp. 243-259 ◽  
Author(s):  
Salam Hajjar ◽  
Emil Dumitrescu ◽  
Laurent Pietrac ◽  
Eric Niel
Keyword(s):  
Reusable Components ◽  
Control Command ◽  
Safe Control ◽  
Command Systems

scholarly journals VINCI®, the european reference for ariane 6 upper stage cryogenic propulsive system

2019 ◽  
Author(s):  
P. Alliot ◽  
J.-F. Delange ◽  
V. De Korver ◽  
J.-M. Sannino ◽  
A. Lekeux ◽  
...  
Keyword(s):  
High Performance ◽  
Design Review ◽  
Design Concepts ◽  
Critical Design ◽  
Potential Applications ◽  
Upper Stage ◽  
Command Systems ◽  
Engine Development ◽  
Orbital Spacecraft ◽  
Government Level

The intent of this publication is to provide an overview of the development of the VINCI® engine over the period 2014–2015. The VINCI® engine is an upper stage, cryogenic expander cycle engine. It combines the required features of this cycle, i. e., high performance chamber cooling and high performance hydrogen turbopump, with proven design concepts based on the accumulated experience from previous European cryogenic engines such as the HM7 and the VULCAIN®. In addition, its high performance and reliability, its restart and throttle capability offer potential applications on various future launcher upper stages as well as orbital spacecraft. At the end of 2014, the VINCI® successfully passed the Critical Design Review that was held after the major subsystem (combustion chamber, fuel and oxygen turbopump) had passed their own Critical Design Review all along the second half of 2014. In December, a Ministerial Conference at government level gave priority to the Ariane 6 program as Europe future launcher. In the framework of this decision, VINCI® was confirmed as the engine to equip Ariane 6 cryogenic upper stage engine. This publication shows how the VINCI development is progressing toward qualification, and also how the requirements of the new Ariane 6 configuration taken into account, i. e., offering new opportunities to the launch system and managing the new constraints. Moreover, the authors capitalize on the development already achieved for the evolution of Ariane 5. In parallel to completing the engine development and qualification, the configuration and the equipment of the propulsive system for Ariane 6 such as the components of the pressurization and helium command systems, board to ground coupling equipment, are being defined.

Assessing the impact of components on future military command systems

2003 ◽  
Vol 10 (4) ◽  
pp. 355-366
Author(s):  
A. Ben‐Dyke ◽  
M. Cusack ◽  
P. Hoare ◽  
M. Lycett ◽  
R.J. Paul
Keyword(s):  
Military Command ◽  
Command Systems ◽  
The Impact

scholarly journals Flight Control Design for a Tailless Aircraft Using Eigenstructure Assignment

2011 ◽  
Vol 2011 ◽  
pp. 1-13 ◽  
Author(s):  
Clara Nieto-Wire ◽  
Kenneth Sobel
Keyword(s):  
Control System ◽  
Flight Control ◽  
Eigenstructure Assignment ◽  
Flight Control System ◽  
Nonlinear Simulation ◽  
Thrust Vectoring ◽  
Stability Margins ◽  
Gain Margin ◽  
Command Systems ◽  
Tailless Aircraft

We apply eigenstructure assignment to the design of a flight control system for a wind tunnel model of a tailless aircraft. The aircraft, known as the innovative control effectors (ICEs) aircraft, has unconventional control surfaces plus pitch and yaw thrust vectoring. We linearize the aircraft in straight and level flight at an altitude of 15,000 feet and Mach number 0.4. Then, we separately design flight control systems for the longitudinal and lateral dynamics. We use a control allocation scheme with weights so that the lateral pseudoinputs are yaw and roll moment, and the longitudinal pseudoinput is pitching moment. In contrast to previous eigenstructure assignment designs for the ICE aircraft, we consider the phugoid mode, thrust vectoring, and stability margins. We show how to simultaneously stabilize the phugoid mode, satisfy MIL-F-8785C mode specifications, and satisfy MIL-F-9490D phase and gain margin specifications. We also use a cstar command system that is preferable to earlier pitch-rate command systems. Finally, we present simulation results of the combined longitudinal/lateral flight control system using a full 6DOF nonlinear simulation with approximately 20,000 values for the aerodynamic coefficients. Our simulation includes limiters on actuator deflections, deflection rates, and control system integrators.

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