Physicians all through the world visit patients under Time limitations. The most important troubled clinical skill under "Time Constraint" is the diagnostic approach. In this situation, clinicians need some diagnostic approaches to reduce both diagnostic Time and errors. It seems that highly experienced physicians utilize some special tactics in this regard. Evidence- based medicine (EBM) as a relatively new paradigm for clinical practice stresses on using research evidences in diagnostic evaluations. The authors aimed to evaluate experts' strategies and assess what EBM can add to these tactics.They reviewed diagnostic strategies of some veteran internists in their busy outpatient clinics and proposed an evidence- based diagnostic model engaging clinical experience and research evidence. It appears that every clinician utilizes a set of "key pointer" questions for decision-making. In addition to use of evidence-based resources for making differential diagnosis and estimating utility of various diseases, clinicians should use "key pointers" with significant likelihood ratios and from independent systems to reduce Time and errors of history taking. Clinical trainees can improve their practice by constructing their own set of pointers from valid research evidences. Using this diagnostic model, EBM can help physicians to struggle against their "Time Constraint".

Orbital transfers are an inevitable part of space missions. An optimal impulsive maneuver is one that consumes the minimum amount of energy to accomplish the transfer. The problem of optimal impulsive orbital 3D maneuver has been the subject of very few published researches due to its particular complications. Finding the optimized solution to this problem needs innovations in every aspect. However, this paper tries to turn this special kind of transfer into an applicable concept. In this paper, optimization equations to express the geometry of initial, target and transfer orbits with respect to each other are derived using the spherical trigonometry. Moreover, several cases for positioning the initial and target orbits relative to each other are presented. Based on actual applications, the problem is solved for both unconstrained and Time-constrained cases. Comprising several local minimums is a characteristic of this optimization problem; consequently, variations of the delta-V are presented as a function of independent variables to achieve the general solution. The numerical results for the optimal impulsive orbital 3D maneuver are presented for a case study, and it is verified by comparing the results in a particular case with those from the Lambert problem. The illustrated results show the appropriate accuracy of the derived equations and performed computations.

In this paper, the Time-optimal control for point-to-point motion of robotic manipulators, with fixed initial and final states, bounded control inputs and jerk Constraint for entire path is presented. First, the jerk Constraint with respect to state variables is derived. Afterwards the dynamic equations of robotic manipulator in state space form and jerk Constraints discretized by forward difference technique. Thus the Time-optimal control problem is formulated as a constrained parameter optimization problem. The MATLAB optimization toolbox is used to obtain the solution of the constrained parameter optimization problem. The proposed method can help us to implement the Time-optimal control problem with bounded inputs and jerk Constraint. Finally, the above-mentioned method is implemented for a 2R planar robotic manipulator. Simulation results show a smooth trajectory for robot motion when the jerk is limited, which can effectively reduce mechanical wear at joints.

A numerical dynamic-aerodynamic interface for simulating the separation dynamics of constrained strap-on boosters jettisoned in the atmosphere is presented. Two commercial solvers: a 6DOF multi-body dynamic solver and a numerical Time-dependent flow solver are integrated together with an interface code to constitute a package that presents real-Time dynamic/aerodynamic coupled analysis. Dynamic unstructured mesh approach is employed using local remeshing methods in respect of bodies motion with a second-order upwind accurate 3D Euler solver. This interface can simulate multi body separation dynamics interaction with aerodynamic effects to complete separation mechanisms like springs, thrusters, joints and so on. The flow solver is validated by the Titan IV launch vehicle experimental data. The separation integration is used for a typical launch vehicle with two strap-on boosters using spring ejector mechanism and spherical Constraint joints acting in the dense atmosphere. Hence, the aim of the presented interface is to facilitate the integration of complicated separation mechanisms with a full numerical CFD aerodynamic solver.