Green Gelled Propellant Gas Generator for High-Performance Divert- and Attitude Control Systems

2016 ◽  
Author(s):  
Karl W. Naumann ◽  
Guiseppe Tussiwand
Keyword(s):  
Control Systems ◽  
Attitude Control ◽  
High Performance ◽  
Gas Generator ◽  
Gelled Propellant

Matlab and Parallel Computing

2012 ◽  
Vol 17 (4) ◽  
pp. 207-216 ◽  
Author(s):  
Magdalena Szymczyk ◽  
Piotr Szymczyk
Keyword(s):  
Image Processing ◽  
Signal Processing ◽  
Parallel Computing ◽  
Distributed Computing ◽  
Control Systems ◽  
High Performance ◽  
Parallel Applications ◽  
Process Simulations ◽  
Key Features ◽  
Financial Process

Abstract The MATLAB is a technical computing language used in a variety of fields, such as control systems, image and signal processing, visualization, financial process simulations in an easy-to-use environment. MATLAB offers "toolboxes" which are specialized libraries for variety scientific domains, and a simplified interface to high-performance libraries (LAPACK, BLAS, FFTW too). Now MATLAB is enriched by the possibility of parallel computing with the Parallel Computing ToolboxTM and MATLAB Distributed Computing ServerTM. In this article we present some of the key features of MATLAB parallel applications focused on using GPU processors for image processing.

A study into the feasibility of using the oxygen-hydrocarbon engine 11D58M as a basis for development of a high-performance multifunctional gas-generatorless rocket engine with oxygen cooling

2019 ◽  
pp. 67-80
Author(s):  
Boris A. Sokolov ◽  
Nikolay N. Tupitsyn
Keyword(s):  
Film Cooling ◽  
High Performance ◽  
Rocket Engine ◽  
Hydrocarbon Fuel ◽  
Gas Generator ◽  
Automatic Equipment ◽  
The Us ◽  
Upper Stage ◽  
Pump Assembly ◽  
Turbo Pump

The paper presents results of engineering studies and research and development efforts at RSC Energia to analyze and prove the feasibility of using the mass-produced oxygen-hydrocarbon engine 11D58M with 8.5 ton-force thrust as a basis for development of a high-performance multifunctional rocket engine with oxygen cooling and 5 ton-force thrust, which is optimal for upper stages (US), embodying a system that does not include a gas generator. The multi-functionality of the engine implies including in it additional units supporting some functions that are important for US, such as feeding propellant from US tanks to the engine after flying in zero gravity, autonomous control of the engine automatic equipment to support its firing, shutdown, adjustments during burn and emergency protection in case of off-nominal operation, as well as generating torques for controlling the US attitude and stabilizing it during coasting, etc. Replacing conventional engine chamber cooling that uses high-boiling hydrocarbon fuel with the innovative oxygen cooling makes it possible to get rid of the internal film cooling circuits and eliminate their attendant losses of fuel, while the use of the oxygen gasified in the cooling circuit of the chamber to drive the turbo pump assembly permits to design an engine that does not have a gas generator. Key words: Multifunctional rocket engine, oxygen cooling, gas-generatorless design, upper stage.

Surrogate models for high performance control systems in wind-excited tall buildings

2020 ◽  
Vol 90 ◽  
pp. 106133 ◽  
Author(s):  
Laura Micheli ◽  
Jonathan Hong ◽  
Simon Laflamme ◽  
Alice Alipour
Keyword(s):  
Control Systems ◽  
High Performance ◽  
Tall Buildings ◽  
Surrogate Models ◽  
Performance Control

Advanced Technology Programs for Small Turboshaft Engines: Past, Present, Future

1991 ◽  
Vol 113 (1) ◽  
pp. 33-39 ◽  
Author(s):  
E. T. Johnson ◽  
H. Lindsay
Keyword(s):  
United States Army ◽  
High Performance ◽  
The United States ◽  
Modern Technology ◽  
Advanced Technology ◽  
Gas Generator ◽  
Turbine Engine ◽  
Technology Programs ◽  
Aircraft Propulsion System ◽  
Year 2000

This paper addresses approximately 15 years of advanced technology programs sponsored by the United States Army Aviation Applied Technology Directorate and its predecessor organizations and conducted by GE Aircraft Engines (GEAE). Included in these programs is the accomplishment of (1) the 1500 shp demonstrator (GE12), which led to the 1700, and (2) the 5000 shp Modern Technology Demonstrator Engine (MTDE/GE27). Also included are several advanced technology component programs that have been completed or are ongoing through the early 1990s. The goals for the next generation of tri-service small advanced gas generator demonstration programs are shown. A prediction is thus made of the advancements required to fulfill the aircraft propulsion system established by the DoD/NASA Integrated High-Performance Turbine Engine Technology (IHPTET) initiative through the year 2000.

Direct Longitudinal Force Feedback for High-Performance Vehicle Dynamics Control Systems

2021 ◽  
Author(s):  
Giorgio Riva ◽  
Luca Mozzarelli ◽  
Matteo Corno ◽  
Simone Formentin ◽  
Sergio M. Savaresi
Keyword(s):  
Model Predictive Control ◽  
Control Systems ◽  
Predictive Control ◽  
Vehicle Dynamics ◽  
High Performance ◽  
Force Feedback ◽  
Longitudinal Force ◽  
Spiral Path ◽  
Comparable Performance ◽  
Vehicle Dynamics Control

Abstract State of the art vehicle dynamics control systems do not exploit tire road forces information, even though the vehicle behaviour is ultimately determined by the tire road interaction. Recent technological improvements allow to accurately measure and estimate these variables, making it possible to introduce such knowledge inside a control system. In this paper, a vehicle dynamics control architecture based on a direct longitudinal tire force feedback is proposed. The scheme is made by a nested architecture composed by an outer Model Predictive Control algorithm, written in spatial coordinates, and an inner longitudinal force feedback controller. The latter is composed by four classical Proportional-Integral controllers in anti-windup configuration, endowed with a suitably designed gain switching logic to cope with possible unfeasible references provided by the outer loop, avoiding instability. The proposed scheme is tested in simulation in a challenging scenario where the tracking of a spiral path on a slippery surface and the timing performance are handled simultaneously by the controller. The performance is compared with that of an inner slip-based controller, sharing the same outer Model Predictive Control loop. The results show comparable performance in presence of unfeasible force references, while higher robustness is achieved with respect to friction curve uncertainties.

Research on Attitude Control of Spacecraft Based on ADRC

2011 ◽  
Vol 383-390 ◽  
pp. 358-365 ◽  
Author(s):  
Fu Lin Teng ◽  
Hong Yu Ge ◽  
Hong Sheng Li ◽  
Jian Hua Zhang
Keyword(s):  
Attitude Control ◽  
Disturbance Rejection ◽  
High Performance ◽  
Control Technology ◽  
Attitude Control System ◽  
Active Disturbance Rejection ◽  
Disturbance Rejection Control ◽  
Simulation And Experiment ◽  
Attitude Controller ◽  
Very High

Modern spacecraft demands from an attitude control system very high performance and accuracy, and many new features, such as disturbance rejection capability. The recently developed active disturbance rejection control technology is applied to the attitude control of spacecraft subject to disturbances and parametric uncertainties. Simulation and experiment show significant advantages of the proposed attitude controller over the controller resulting from conventional PID approach.

Control moment gyroscopes for spacecraft attitude control systems: Current status and prospects

2015 ◽  
Vol 6 (3) ◽  
pp. 236-240 ◽  
Author(s):  
A. R. Mkrtychyan ◽  
N. I. Bashkeev ◽  
D. O. Yakimovskii ◽  
D. I. Akashev ◽  
O. B. Yakovets
Keyword(s):  
Control Systems ◽  
Attitude Control ◽  
Current Status ◽  
Spacecraft Attitude ◽  
Spacecraft Attitude Control ◽  
Control Moment ◽  
Control Moment Gyroscopes
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