In the common practice of designing an attitude tracker for an aerospacecraft, one transforms the Newton-Euler rotation equations to obtain the dynamic equations of some chosen inertial frame based attitude metrics, such as Euler angles and unit quaternions.
An evaluation research design based on a conceptual framework for measuring knowledge and attitude was developed and implemented using a pretest-intervention-posttest approach for 15% of the study population of 750 inpatient registered oncology nurses.
The methodology redefines the ultimate goal of design based on the qualitative notion of satisfaction, and formalizes the effect of designer's subjective attitude in the process.
An adaptive fault tolerant nonlinear control design based on the theory of sliding mode is proposed to control the attitude of a satellite using solar radiation pressure.
They can design based on instinct.
Unlike conventional remote sensing satellites, which are designed based on three-axis attitude control systems, in this paper, the design is based on a spin stabilized satellite.
The multi-objective controller is designed based on linear model of attitude dynamics.
Firstly, a reentry guidance law is designed to generate feasible guidance commands which are then tracked by second-order sliding mode attitude controller designed based on quasi-continuous high-order sliding mode theory.
Subsequently, the single-antenna GPS/SINS integrated navigation system is designed based on the combination of position, velocity, and attitude.
First, a finite-time filter is proposed to generate the pseudo-angular-velocity signal, which is fed to the controller, and then a continuous finite-time attitude controller is designed based on the proposed filter.
With this purpose, at first, a cascade control strategy including two closed loops is considered to be designed based upon the full quaternion based three-axis finite-time attitude control approach.
