STOL Tactical Aircraft Investigation. Volume V. Part I. Flight Control Technology: System Analysis and Trade Studies for a Medium STOL Transport with Vectored Thrust/Mechanical Flaps

1973 ◽  
Author(s):  
Kenneth J. Crandall ◽  
David J. Maund ◽  
William E. Gerken ◽  
James H. Vincent
Keyword(s):  
Flight Control ◽  
System Analysis ◽  
Control Technology ◽  
Technology System ◽  
Vectored Thrust

scholarly journals Research and Application of One-key Sequence Control Technology for Substations

2019 ◽  
Vol 136 ◽  
pp. 01022
Author(s):  
Ge Li-Qing ◽  
Wang Jian-Feng ◽  
Teng Jing-Yu ◽  
Yang Ming
Keyword(s):  
Decision Support ◽  
Background Information ◽  
Control Technology ◽  
Technology System ◽  
Management Efficiency ◽  
Electrical Grids ◽  
Effectiveness And Efficiency ◽  
The One ◽  
Reasonable Use ◽  
Overall Effectiveness

The substations are important parts of modern electrical grids. In this sense, it is necessary to enhance the management efficiency and robustness of the substations. The one-key sequence control technology system could simultaneously control several subsystems and make use of their functions to automatically operate the substations. In this study, three subsystems, i.e., monitoring subsystems, error analysis subsystem, and decision support subsystem are designed in the one-key sequence control technology system. All the background information from the substations is monitored, checked, detected to find the potential threats. The decision support subsystem provides suggestive ways to handle these problems. Therefore, through the reasonable use of the one-key sequence control technology, the overall effectiveness and efficiency of the substations can be enhanced. With the development of artificial intelligence technologies, the one-key sequence control technology system can be further improved with more powerful functions.

Roll aerodynamic characteristics study of an unmanned aerial vehicle based on circulation control technology

2017 ◽  
Vol 233 (3) ◽  
pp. 871-882
Author(s):  
Kun Chen ◽  
Zhiwei Shi ◽  
Jiachen Zhu ◽  
Haiyang Wang ◽  
Junquan Fu
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Flight Control ◽  
Attitude Control ◽  
Aerodynamic Force ◽  
Flight Test ◽  
Scale Model ◽  
Maximum Efficiency ◽  
Control Technology ◽  
Circulation Control ◽  
Aerial Vehicle

To explore the control efficiency of circulation flow control technology, a circulation control actuator with an independent gas source has been designed and applied in roll attitude control of a small unmanned aerial vehicle. The circulation control devices are arranged at the two ends of the wing on an unmanned aerial vehicle scale model, the changes in aerodynamic force and aerodynamic moment caused by turning on the actuator are measured in a wind tunnel, and the flow field characteristics are analysed using particle image velocimetry technology. The flight control effect of the roll attitude is verified via a flight test. Experimental and flight test results show that the control of roll attitude can be achieved by turning on the circulation control actuator on one side, and the maximum efficiency that the circulation control generates is equivalent to 8° aileron deflection with production of a favorable yaw moment to achieve a coordinated turn. The circulation control actuator can increase lift and reduce drag when opened on both sides simultaneously. The maximum lift-to-drag ratio of the UAV increased from 5 to 9, and this approach can also suppress flow separation and delay stall at high angles of attack. The aileron or trailing edge flaps can be replaced with circulation control actuators, and the circulation control technology can also be applied to aerodynamic performance improvement and flight control in other types of aircraft.

Application of Agile Model-Based Systems Engineering in aircraft conceptual design

2019 ◽  
Vol 123 (1268) ◽  
pp. 1561-1601 ◽  
Author(s):  
G. P. Krupa
Keyword(s):  
Systems Engineering ◽  
Flight Control ◽  
System Analysis ◽  
Object Oriented ◽  
Aircraft Design ◽  
System Engineering ◽  
Smooth Transition ◽  
Model Based ◽  
Agile Model ◽  
Aircraft Conceptual Design

ABSTRACTOne of the challenges of modern engineering design is the amount of data that designers must keep track while performing system analysis and synthesis. This task is particularly important in the design process of complex systems such as novel aerospace systems where Modeling and Simulation play an essential role. The Agile philosophy stems from the field of Software Engineering and describes an approach to development in which requirements and solutions gradually develop through collaboration between self-organising cross-functional teams and end users. Agile Model-Based System Engineering (AMBSE) is the application of the Agile philosophy to Model-Based System Engineering. In this paper, AMBSE is accomplished through the application of the Object-Oriented System Engineering Method (OOSEM). OOSEM employs a top-down scenario-driven process that adopts System Modeling Language (SysML) and leverages the object-oriented paradigm to support the analysis, specification, design, and verification of systems. AMBSE assisted by mathematical modelling and safety assessment techniques is applied to the first design iterations of the main aircraft systems, allowing a comprehensive design exploration. The flight control system was chosen to illustrate the procedure in detail, emphasising the synthesis of a six-degrees-of-freedom model augmented by dynamic inversion control for a hypothetical supersonic transport aircraft satisfying class II MIL-F-8785C handling qualities. It is concluded that AMBSE presents promising properties to support future aircraft development within the current regulatory framework for aircraft design, while enabling a smooth transition from conceptual to preliminary design.

Research on Machining Methods for Non-Circular Isometric Profile

2009 ◽  
Vol 407-408 ◽  
pp. 68-72
Author(s):  
Hong Yan Wang ◽  
Xue Feng Yang ◽  
Pei Quan Guo
Keyword(s):  
Design Principle ◽  
Damping Ratio ◽  
Numerical Control ◽  
Control Technology ◽  
Servo Motor ◽  
Technology System ◽  
Modeling Technology ◽  
Value Range ◽  
Machining System ◽  
Profile Modeling

Two machining methods for non-circular isometric profile are introduced. The profile modeling technology and the numerical control technology are analyzed. The dynamic property of in a series profile modeling technology system is revealed, and the design principle for in a series profile modeling technology system is put forward, the value range of damping ratio is instanced at near 0.7. The turning machining system adopting linear servo motor as drive element is brought forward.

scholarly journals Survey on Flight Control Technology for Large-Scale Helicopter

2017 ◽  
Vol 2017 ◽  
pp. 1-14 ◽  
Author(s):  
Jinshuo Hu ◽  
Hongbin Gu
Keyword(s):  
Flight Control ◽  
Large Scale ◽  
Control Technology ◽  
Flight Control System ◽  
Future Directions ◽  
Research Issues ◽  
Advantages And Disadvantages ◽  
Helicopter Flight ◽  
Challenging Research ◽  
Theoretical Developments

A literature review of flight control technology is presented for large-scale helicopter. Challenges of large-scale helicopter flight control system (FCS) design are illustrated. Following this, various flight control methodologies are described with respect to their engineering implementation and theoretical developments, whose advantages and disadvantages are also analyzed. Then, the challenging research issues on flight control technology are identified, and future directions are highlighted.

Advanced flight control technology achievements at Boeing Helicopters

1994 ◽  
Vol 59 (1) ◽  
pp. 263-290 ◽  
Author(s):  
KENNETH H. LANDIS ◽  
JAMES M. DAVIS ◽  
CHARLES DABUNDO ◽  
JAMES F. KELLER
Keyword(s):  
Flight Control ◽  
Control Technology

Carefree Handling Systems for Helicopters

1992 ◽  
Vol 206 (1) ◽  
pp. 37-46 ◽  
Author(s):  
C P Massey
Keyword(s):  
Control Systems ◽  
Active Control ◽  
Flight Control ◽  
Control Technology ◽  
Visual Displays ◽  
Tactile Cues

A programme of work is being undertaken with the aim of defining features to help the pilot respect the helicopter's numerous flight limitations, reducing the workload and enhancing mission performance. Carefree handling features that have been studied include visual, audible and tactile cues and direct intervention methods. These features have been evaluated in a series of piloted simulation trials at DRA Bedford. Most of the work to date has been based around helicopters with active control technology (ACT) flight control systems, but conventionally controlled helicopters have also been considered. Results from the programme suggest some benefits for head-up visual displays, tactile and audible cues, with more significant benefits for the direct intervention methods. A combination of these features allows the pilot to use the full performance of the vehicle without exceeding limits and at low pilot workload.

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