Development of flight control system for 2D differential geometric guidance and control problem

This paper, which was presented at an Institute meeting held in London on 21 January 1970, suggests a range of philosophical implications which result from the interaction of guidance and control systems in the context of all-weather landing of fixed-wing aircraft. It then attempts to deduce the considerations which must be applied to the approach to the engineering solution to the guidance and control problem.In the context of this paper the terms guidance and control have specialized connotations which have achieved the status of common usage.As they are used in the all-weather operations (AWO) jargon they are easier to define as adjectives than as nouns; the ‘guidance system’ is the system which defines the flight-path which the landing aircraft must follow and the ‘control system’ is that part of the aircraft equipment which enables the aircraft to follow the flight-path which has been defined by the guidance system.

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Study of Low Cost Micro Autopilot for Fixed-Wing UAV

Advanced Materials Research ◽

10.4028/www.scientific.net/amr.317-319.1672 ◽

2011 ◽

Vol 317-319 ◽

pp. 1672-1676

Author(s):

Wei Xiong ◽

Zhao Ying Zhou ◽

Xiao Yan Liu

Keyword(s):

Control System ◽

Flight Control ◽

Low Cost ◽

Cost Effective ◽

System Structure ◽

Gps Receiver ◽

Flight Control System ◽

Sensor Configuration ◽

The Cost ◽

And Control

From the cost-effective viewpoint of low cost Bank-to-Turn (BTT) Unmanned Air Vehicles (UAV) and target drone, a low cost flight control system, with the fewest number of sensors, is studied in this paper for the fixed-wing UAV. The structure of the control system is described which is able to estimate necessary information to provide stabilization and guidance for a small fixed wing BTT UAV. The practical flight control system structure and control law for roll hold loop, altitude hold loop, trajectory tracking loop are designed based on the sensor configuration with only a MEMS rate gyro, a MEMS pressure sensor and global positioning system (GPS) receiver only. A prototype low cost autopilot is trial-produced to control a typical UAV. The Experimental results show the effectiveness of navigation and control methods of f the proposed methodology.

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DESIGN AND CONTROL SYSTEM OF THE ROBOT ORNITHOPTER, EQUIPPED WITH WINGS AND TAIL

Proceedings of Southwest State University ◽

10.21869/2223-1560-2018-22-2-18-26 ◽

2018 ◽

Vol 22 (2) ◽

pp. 18-26 ◽

Cited By ~ 1

Author(s):

S. F. Jatsun ◽

О. G. Loktionova ◽

L. Yu. Vorochaeva ◽

О. V. Emelianova

Keyword(s):

Control System ◽

Flight Control ◽

Control Unit ◽

Longitudinal Axis ◽

Control Device ◽

Control Area ◽

The Body ◽

Flight Control System ◽

Spherical Hinge ◽

And Control

The paper deals with the ornithopter flight which simulates the flight of a bird. The robot consists of a body, two folding wings and a tail. The ornithopter roll is provided by wing swings, and pitch and yaw are provided by twists of the tail in two planes. When switching to the design scheme of the device, each wing is replaced by two links connected to each other and to the body by means of cylindrical hinges, the axes of all hinges are parallel to the longitudinal axis of the robot. Two mechanisms are used to implement swings in the device. One of them (the mechanism of swings) directly provides fluctuations in the wings relative to the body, as well as changing their area by adding when moving up and decomposition when moving down. This mechanism consists of a motor and crank-rod-rocker mechanism. The second mechanism (rotation of the ailerons on the wings) allows the wings in addition to flapping additionally to flex during motion, thereby "pocketing" of the air and the extra control area of the wings: its decrease with the movement of the wings up and the increase in the movement of the wings down. The tail is connected to the body due to the spherical hinge and two crank mechanisms. With the help of one of the mechanisms the tail rotates relative to the longitudinal axis of the body in the horizontal plane, and with the help of the other - in the vertical. For this robot a flight control system is proposed, which provides the robot movement along a given trajectory. The control system includes a control unit and a control device (ornithopter). The control unit is formed by modules specifying the effects and calculation of angles, as well as comparator and controller. The control device includes drives, links (wings and tail) and the robot body. Management is carried out on six generalized coordinates determining the position and orientation of the hull in space. For this purpose, eight feedbacks are used in the angles of rotation of the wings and the tail of the robot relative to its body.

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