Eigenvalue and control-law trajectories for a turboalternator model under fault conditions

1968 ◽  
Vol 4 (1) ◽  
pp. 9-12
Author(s):  
H. Nicholson
Keyword(s):  
Control Law ◽  
And Control

Effect and Control of Pendular Motion of Abandoned Satellite on Tether Drag System

2014 ◽  
Vol 513-517 ◽  
pp. 3900-3906
Author(s):  
Guo Wei Zhao ◽  
Bin Tang ◽  
Liang Sun ◽  
Xing Min Zhang
Keyword(s):  
Space Debris ◽  
Control Method ◽  
Tangential Direction ◽  
Angular Frequency ◽  
Tension Control ◽  
Control Law ◽  
Attitude Dynamics ◽  
Jet Control ◽  
And Control ◽  
Oscillation Characteristics

As a kind of typical on-orbit capture and aberrance technology, space tether de-orbit system has broad application prospect in terms of cleaning space debris and abandoned satellites. In the paper, the attitude dynamics equations of the tether de-orbit system is established based on law of moment of momentum; Against the background of de-orbiting under a constant thrust in the tangential direction, the optimized PD control law with limited attitude feedback on jet control and momentum wheel control is designed for the mission satellite; The oscillation characteristics of the attitude of abandoned satellite are studied, and the effect of the oscillation on the tethered system and based satellite are analyzed; According to the demand for maintaining the position and suppressing the oscillation of the abandoned satellite, a kind of tension control method is put forward. Numerical simulation results indicate that the abandoned satellite oscillates at a specific angular frequency, and the large amplitude threatens the stabilization of tethered system; the designed tension control method effectively eliminate the oscillation of the abandoned satellite and ensure the flight safety of the tether de-orbit system, with economic energy consumption for the control of the based satellite.

A Stochastic Regulator for Integrated Communication and Control Systems: Part II—Numerical Analysis and Simulation

1991 ◽  
Vol 113 (4) ◽  
pp. 612-619 ◽  
Author(s):  
Luen-Woei Liou ◽  
Asok Ray
Keyword(s):  
Control Systems ◽  
Numerical Procedure ◽  
Linear Quadratic Regulator ◽  
State Feedback Control ◽  
Control Law ◽  
Linear Quadratic ◽  
Simulation Experiments ◽  
Integrated Communication ◽  
And Control ◽  
Future Work

A state feedback control law has been derived in Part I [1] of this two-part paper on the basis of an augmented plant model [2, 3, 4] that accounts for the randomly varying delays induced by the network in Integrated Communication and Control Systems (ICCS). The control algorithm was formulated as a linear quadratic regulator problem and then solved using the principle of dynamic programming and optimality. This paper, which is the second of two parts, presents (i) a numerical procedure for synthesizing the control parameters and (ii) results of simulation experiments for verification of the above control law using the flight dynamic model of an advanced aircraft. This two-part paper is concluded with recommendations for future work.

scholarly journals Longitudinal flight control design with handling quality requirements

2006 ◽  
Vol 110 (1111) ◽  
pp. 627-637 ◽  
Author(s):  
D. Saussié ◽  
L. Saydy ◽  
O. Akhrif
Keyword(s):  
Flight Control ◽  
Control Law ◽  
Longitudinal Motion ◽  
Model Order ◽  
Quality Requirements ◽  
Loop Design ◽  
Business Jet ◽  
Stability Augmentation ◽  
Handling Quality ◽  
And Control

Abstract This work presents a method for selecting the gain parameters of a C* control law for an aircraft’s longitudinal motion. The design incorporates various handling quality requirements involving modal, time- and frequency-domain criteria that were fixed by the aircraft manufacturer. After necessary model order-reductions, the design proceeds in essentially two-steps: stability augmentation system (SAS) loop design and control augmentation system (CAS) loop design. The approach partly relies on the use of guardian maps to characterise, in each case, the set of gain parameters for which desired handling quality requirements are satisfied. The approach is applied throughout the full flight envelope of a business jet aircraft and yields satisfactory results.

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