Evolutionary Optimisation of a Flexible-Launcher Simple Adaptive Control System

Attitude control of conventional launchers is relatively easy and straightforward and gives an adequate performance when applied to the nominal vehicle and mission. However, in the presence of environmental disturbances and vehicle design uncertainties, more robust types of controllers are required to guarantee stable attitudes. This chapter...

Active power control of waked wind farms

Active power control can be used to balance the total power generated by wind farms with the power consumed on the electricity grid. With the increasing penetration levels of wind energy, there is an increasing need for this ancillary service. In this paper, we show that the tracking of a certain power reference signal provided by the...

Linear quadratic regulator design for an unpowered, winged re-entry vehicle

DASMAT-Delft University aircraft simulation model and analysis tool: A Matlab/Simulink environment for flight dynamics and control analysis

Control synthesis for linear parametric time-varying systems

Designing auto-pilots with classical controller design methods such as root-locus may be a laborious job and it requires a lot of experience to arrive at satisfactory controllers. The single loop closure techniques that are common practice for most aircraft manufacturers are mainly appreciated because of the vast amount of experience gained in...

The layered safety concept, an integrated approach to the design and validation of air traffic management enhancements

The expected growth of air traffic asks for large enhancements in continental Air Traffic Management (ATM) to increase capacity. From a technology point of view a multitude of 'solutions' are available, such as introducing air-ground datalink, providing better support to the ATCo (Air Traffic Controller), introducing 4D air traffic control,...

Synthesis of local control for a robotic manipulator joint

The objective of the study is the synthesis of an algorithm for the automatic control of an electromechanical actuator in the rotational joint of a multi-link, robotic manipulator. Control performance is assessed in terms of ability of the controlled joint to follow a commanded joint angle, or a commanded joint angular rate. Part One of the...

Frequency response analysis of hybrid systems

Current design methods for digital control systems to be operated in a continuous environment do not always result in the most efficient use of digital computing hardware. To improve this situation, a dedicated frequency response analysis method was developed for hybrid systems. For practical use of the method, it has been expanded to an...

Feasibility demonstration of a sensor for High-Quality two-phase flow

Two-phase flow heat transport systems for the Columbus Space Platform and the Space Station are expected to incorporate systems to control the liquid flow rates into evaporative cold plates. Candidate components for such a control system are sensors monitoring the (very high) mixture quality at the cold plate exit lines, control algorithms and...

Modelling and simulation of a rate controlled manipulator ARM

The mathematical model of a space based manipulator arm with a rate controlled end effector is defined and the recursive algorithms for the computation of the basic djmamic functions are formulated. A digital simulation of this system is implemented and preliminary results are presented. Actual running times for the simulation In a VAX 750...

Study of NAVSAT control segment characteristics: part III: executive summary

On the proposed satellite-based navigation system NAVSAT, a study has been performed concerning the characteristics of the control segment. Starting from the outcome of earlier preliminary studies of ESA, this study shows that the concept is feasible.

Dynamics of flexible spacecraft: an analysis approaches towards mathematical model order reduction

Increases in size and mechanical complexity of spacecraft result in increased complexity of the mathematical model which describes the spacecraft dynamics. This results in turn in increased computational effort, in increased difficulties in understanding the characteristics of the spacecraft dynamics, and in increased difficulties in the design...