Introduction: Inhalation induction is a common method in pediatrics anesthesia . There is not suitable clincial guide for assessmen depth of anesthesia before intubation, in this study adequacy of Jaw thrust as a guide for this assessement was evaluated.Methods: In a clinical trial study 90 pediatric patient, ASA1 & 2, six month to 5 year old age, were divided in case and control groups. Inhalation inductions were done by 4% Halothane, 4lit/min O2 and 4Lit/min N2o under spontaneous ventilation. In case and control groups, Jaw thrust and ordinary methods were utilized respectively for assessment of depth of anesthesia befor intubations. Changes in HR, SpO2, end tidal of halothane and duration of induction, duration of laryngoscopy, reactions to intubations and complications were measured and then analyzed by t - test and Chi squar statistical tests.Results: Duration and complications of larynogscopy were greater in case than control group. Conclusion: Jaw thrust alone is not a good clinical test assessment of depth of anesthesia before intubations in inhalation anesthesia. Probaly one and half to two minutes after negative respones to jaw thrust is a suitable time for intubations in pediatrics inhalation anesthesia .

In line with the current research on the ultimate strength assessment of ship hull girders, careful understanding of the collapse behaviour of unstiffened plate elements within the ship hull girders is an important and necessary task. In this paper, the collapse behaviour of unstiffened plates under longitudinal and transverse thrust is studied by clastoplastic large deflection FEM and the characteristics of the collapse modes are highlighted.

Several optimal three-dimensional orbital transfer problems are solved for thrust-limited spacecrafts using collocation and nonlinear programming techniques. The solutions for full nonlinear equations of motion are obtained where the integrals of the free Keplerian motion in three dimensions are utilized for coasting arcs. In order to limit the solution space, interior-point constraints are used which proved to be beneficial in finding the optimal results by making initial estimates more sensible. The application of this methodology to the design of several three dimensional optimal trajectories is also investigated. The results indicate that the method is suitable for any 3D transfer between non-coplanar and non-coaxial orbits.

A new guidance scheme for the problem of Low-thrust transfer between inclined orbits is developed within the framework of optimal control theory. The objective of the guidance scheme is to provide the appropriate thrust steering program that will transfer the vehicle from an inclined low earth orbits to the high earth orbits. The presented guidance scheme is determined using Pontryagin’s principle such that three desired performance measures are minimized and boundary conditions for this unspecified final time problem are satisfied. One of the novelties of this work is changing independent variable from time to thrust angle and considering properties of autonomous system equations to reduce to one where exact analytical solution is obtained.

Allochthonous masses are common structures in Zagros fold-thrust belt. They are generally considered as collapse structures formed by the influence of gravity and in rock units with competency contrast. However, large allochthonous masses mapped in Dowgonbadan area in Dezful Embayment near the Mountain Front Fault (MFF) of Zagros show characteristics different from the belt common collapse structures. In this paper, the influences of both gravity and thrusting on development of these masses are presented. Evidences such as the volume of the masses, the greater spacing between the masses and their origin, and the occurrence of crushed zone on the base of the masses are considered as criteria to separate these masses from common collapse structures and are classified as thrust related collapse structures. Thus, thrust faults as well as gravity are proposed as the main features controling the development of these types of collapse structures in the Zagros.

Designing space propulsion systems as one of the important subsystems of the spacecrafts and upper stage space launch systems needs to bypass different and complicated steps. In this article the comprehensive process of designing liquid fuel low-thrust space propulsion systems was illustrated. In the presented pattern, first of all according to the requirements and mission constraints, the main characteristics of the system were determined and then other characteristics were extracted. Finally, for the evaluation of the presented pattern, a low- thrust space propulsion system was designed based on a special mission and the results were compared with a real model. Comparison between the designed space propulsion system and the real one showed an appropriate accuracy of the presented pattern.

In this researche, effect of lateral liquid Freon injection on the thrust vector deviation is investigated. For this purpose, variation of different parameters as liquid injection from injector in to the nozzle and its effect on the trust deviation are considered. In this system, some of the most important parameters are; injection mass flow rate, angle injection, position injection and main flow rate from nozzle to the main flow. Simulation of flow field has been done using Fluent 6.2.16 software and for result validation, some experimental data have been used. The results shows that the optimum position of injection is about 35-40 percentage of divergent nozzle length from throat position, angle of injection has negligible effect on deviation of thrust vector and optimum values of mass flow injection depend on position of injection.

In order to solve the problem of insufficient thrust measurement accuracy of aeroengine indoor testbed, the thrust calibration experiment technology is studied. Form two aspects of engine static calibration and dynamic calibration, the mechanism of thrust calibration is comprehensively analyzed form the perspective of testbed and engine, and a complete set of operable test specifications is formed. The technical difficulties of engine consistency, inlet temperature deviation and non-standard weather are solved, and the accuracy of thrust transmission process is ensured. The test scheme of indoor test bed calibration is given, and the corresponding ideas and requirements are given according to the test conditions, test bench, calibration engine, test process and result analysis, to ensure the accuracy of calibration results.