Guidance and control laws design for a switched system with discontinuous actuators

2016 ◽  
Vol 38 (5) ◽  
pp. 829-846 ◽  
Author(s):  
Jian Chen ◽  
Zixuan Liang ◽  
Chen Bai ◽  
Peng Li ◽  
Zhang Ren ◽  
...  
Keyword(s):  
Switched System ◽  
Control Laws ◽  
Guidance And Control ◽  
And Control

scholarly journals Guidance Law and Neural Control for Hypersonic Missile to Track Targets

2016 ◽  
Vol 2016 ◽  
pp. 1-10 ◽  
Author(s):  
Wenxing Fu ◽  
Binbin Yan ◽  
Xiaofei Chang ◽  
Jie Yan
Keyword(s):  
Neural Control ◽  
Controller Design ◽  
Sliding Mode ◽  
External Disturbance ◽  
Control Laws ◽  
Guidance And Control ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Control Command ◽  
And Control

Hypersonic technology plays an important role in prompt global strike. Because the flight dynamics of a hypersonic vehicle is nonlinear, uncertain, and highly coupled, the controller design is challenging, especially to design its guidance and control law during the attack of a maneuvering target. In this paper, the sliding mode control (SMC) method is used to develop the guidance law from which the desired flight path angle is derived. With the desired information as control command, the adaptive neural control in discrete time is investigated ingeniously for the longitudinal dynamics of the hypersonic missile. The proposed guidance and control laws are validated by simulation of a hypersonic missile against a maneuvering target. It is demonstrated that the scheme has good robustness and high accuracy to attack a maneuvering target in the presence of external disturbance and missile model uncertainty.

Guidance and control algorithms for mini UAV autopilots

2017 ◽  
Vol 89 (1) ◽  
pp. 133-144 ◽  
Author(s):  
Elisa Capello ◽  
Giorgio Guglieri ◽  
Gianluca Ristorto
Keyword(s):  
Attitude Control ◽  
Path Following ◽  
Adaptive Controller ◽  
Computationally Efficient ◽  
Control Laws ◽  
Content Type ◽  
Guidance And Control ◽  
Aerial Vehicle ◽  
Set Up ◽  
And Control

Purpose The aim of this paper is the implementation and validation of control and guidance algorithms for unmanned aerial vehicle (UAV) autopilots. Design/methodology/approach The path-following control of the UAV can be separated into different layers: inner loop for pitch and roll attitude control, outer loop on heading, altitude and airspeed control for the waypoints tracking and waypoint navigation. Two control laws are defined: one based on proportional integrative derivative (PID) controllers both for inner and outer loops and one based on the combination of PIDs and an adaptive controller. Findings Good results can be obtained in terms of trajectory tracking (based on waypoints) and of parameter variations. The adaptive control law guarantees smoothing responses and less oscillations and glitches on the control deflections. Practical implications The proposed controllers are easily implementable on-board and are computationally efficient. Originality/value The algorithm validation via hardware in the loop simulations can be used to reduce the platform set-up time and the risk of losing the prototype during the flight tests.

Suboptimal Guidance and Control Design for a Missile with Onboard Strapdown Seeker

2011 ◽  
Vol 110-116 ◽  
pp. 2513-2520
Author(s):  
Netra Singh ◽  
Manoranjan Sinha
Keyword(s):  
Coupling Effect ◽  
Three Dimensional ◽  
Impact Angle ◽  
Terminal Phase ◽  
Dynamic Inversion ◽  
Control Laws ◽  
Guidance And Control ◽  
Guidance Law ◽  
Hamilton Jacobi Bellman ◽  
And Control

Dynamic inversion control in conjunction with nonlinear suboptimal three dimensional (3-D) guidance law, in terminal phase, is implemented in both the pitch and yaw plane for a short range surface to surface missile with onboard active strapdown seeker. The implemented guidance and control laws intercept the target with a minimum miss distance in addition to meeting the various constraints such as line of sight, seeker field-of-view (FOV), and impact angle. This is achieved using approximate solution to Hamilton-Jacobi-Bellman (HJB) equation [1]. Dynamic inversion control is implemented in two time scales for the inner loop body rate and outer loop angles. Various nonlinearities including that due to the coupling effect between pitch and yaw channels are accounted for in the six-degree-of-freedom (6-DOF) formulation.

Optimizing the Guidance and Control Laws at the Space Optoelectronic Observation

2011 ◽  
Vol 44 (1) ◽  
pp. 2078-2083 ◽  
Author(s):  
S. Somov ◽  
Ye. Somov ◽  
S. Butyrin ◽  
A. Butko
Keyword(s):  
Control Laws ◽  
Guidance And Control ◽  
And Control

scholarly journals SATELLITE GUIDANCE AND CONTROL DURING OPERATIVE OPTOELECTRONIC IMAGERY FOR DISASTER MANAGEMENT

2018 ◽  
Vol XLII-3/W4 ◽  
pp. 475-482
Author(s):  
Y. Somov ◽  
C. Hajiyev
Keyword(s):  
Disaster Management ◽  
Attitude Control ◽  
Attitude Determination ◽  
Earth Surface ◽  
Attitude Control System ◽  
Control Laws ◽  
Guidance And Control ◽  
The Earth ◽  
Synchronous Orbit ◽  
And Control

<p><strong>Abstract.</strong> We consider problems on surveying the Earth surface during operative optoelectronic imagery for disaster management with respect to attitude guidance and control of the agile spacecraft. The land surveying is carried out by a set of extended orthodromic routes of scanning optoelectronic observation for a given part of the Earth surface. We present developed methods for synthesis of nonlinear guidance and attitude control laws, dynamic research of the spacecraft attitude control system with the satellite astroinertial attitude determination and digital control by the excessive gyro moment cluster. We present results on the efficiency of the developed vector spline guidance laws, algorithms for discrete filtering and the digital gyromoment control of a satellite orientation during the areal landsurveying of Istanbul neighborhoods for the spacecraft on sun-synchronous orbit with altitude of 720&amp;thinsp;km when the allowed deviation of the target line from Nadir is within the cone with semi-angle of 40&amp;thinsp;deg.</p>

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