The strengthening of Islamic values on students through the metaphor of accepting death: an Indonesian perception

Death is a sure entity for every human that cannot be avoided in human life. The purpose of this research was to reveal that the usage of metaphor technique called, “The Acceptance of Death” in group counselling can improve Islamic values on Muslim students. This study employed an action research using The Kemmis Model with the stages of planning, action, observation, and reflection. This research implemented group counselling with metaphor technique of accepting death by students. The research subjects were 20 female students of State Islamic University of Sultan Syarif Kasim Riau who lived in the campus dormitory. The selection of the research subjects was done randomly by choosing the female students who were willing to join the group counselling activity. The research results showed that the practice of metaphor technique of “The Acceptance of Death” in the group counselling can strengthen the Islamic values and their characteristics as Muslims. They understand their previous mistakes and are willing to be better for the sake of their life. They have the commitment to become the best students and the best Muslims

Orbiting Geophysical Observatory Attitude Control Subsystem design survey

Development history and design modifications for attitude control subsystem of OG

Design of a Tracking Glove for use in Virtual Reality Training Environments

A thesis presented to the faculty of the College of Business and Technology at Morehead State University in partial fulfillment of the requirements for the degree Master of Science by Thomas A. Buteyn on April 25, 2022

Apollo guidance, navigation and control - Design survey of the Apollo inertial subsystem

Design, development, and testing of inertial guidance and navigation systems for Apollo projec

High-Accuracy and Fast-Response Flywheel Torque Control

Compared with current mode flywheel torque controller, speed mode torque controller has superior disturbance rejection capability. However, the speed loop delay reduces system dynamic response speed. To solve this problem, a two-degrees-of-freedom controller (2DOFC) which consists of a feedback controller (FBC) and a command feedforward controller (FFC) is proposed. The transfer function of FFC is found based on the inverse model of motor drive system, whose parameters are identified by recursive least squares (RLS) algorithm in real-time. Upon this, Kalman filter with softening factor is introduced for the improved parameters identification and torque control performances. Finally, the validity and the superiority of the proposed control scheme are verified through experiments with magnetically suspended flywheel (MSFW) motor

The NASA/JPL 64-meter-diameter antenna at Goldstone, California: Project report, technical staff, tracking and data acquisition organization

The significant management and technical aspects of the JPL Project to develop and implement a 64-meter-diameter antenna at the Goldstone Deep Space Communications Complex in California, which was the first of the Advanced Antenna Systems of the National Aeronautics and Space Administration/Jet Propulsion Laboratory Deep Space Network are described. The original need foreseen for a large-diameter antenna to accomplish communication and tracking support of NASA's solar system exploration program is reviewed, and the translation of those needs into the technical specification of an appropriate ground station antenna is described. The antenna project is delineated by phases to show the key technical and managerial skills and the technical facility resources involved. There is a brief engineering description of the antenna and its closely related facilities. Some difficult and interesting engineering problems, then at the state-of-the-art level, which were met in the accomplishment of the Project, are described. The key performance characteristics of the antenna, in relation to the original specifications and the methods of their determination, are stated

Development and Testing of a Steerable Cruciform Parachute System

Title from PDF of title page viewed June 18, 2018Thesis advisor: Travis FieldsVitaIncludes bibliographical references (pages 93-99)Thesis (M.S.)--School of Computing and Engineering. University of Missouri--Kansas City, 2018This thesis focuses on the development of a parachute payload system which is capable of precision aerial delivery yet only represents a modest cost increase over ballistic unguided systems. In order to develop such a system, first a canopy is selected. The canopy should be simple and inexpensive to make; in this case a cruciform canopy was selected because this design is material efficient and requires far less labor to manufacture compared to parafoil parachutes. Next some method of stabilizing that canopy during flight must be proposed. In this case, the system heading is to be stabilized via a single actuator by asymmetric deflection of the leading edge of one canopy panel. At this stage in the development, a controller must be designed and implemented which stabilizes the system in the proposed way. Outdoor flight testing is the gold standard of parachute testing methodology since it offers the most realistic flight conditions. However, the unmeasured wind disturbances encountered in outdoor flight testing can confound results and interfere with repeatability of experiments. The first experiment explained in this thesis revolves around the testing of a steer able cruciform parachute system using a vertical wind tunnel. The primary goal of the experiment was to develop a heading stabilizing controller. Additionally, a closed-loop system model was identified and a technique was developed for estimating canopy glide ratio (GR). The vertical wind tunnel testing methodology is far faster and less expensive than the outdoor flight testing which would be needed to accomplish the same goals. After proving that a system can be steered via the proposed methodology, the next stage in the developing of a precision guided vehicle is to demonstrate that the stabilization technique is viable. This is accomplished in both outdoor flight testing and a simulation based on the closed-loop model identified earlier. Furthermore, the precision navigation potential of the system must be demonstrated; specifically, the system must be capable of arriving closer to the desired impact point on the ground than an unguided system dropped under the same conditions. The work described in this thesis has advanced the development of the steerable cruciform parachute system beyond the point of simply being a feasibility demonstrator. The vertical wind tunnel experiments demonstrated that the system heading could be stabilized and subsequent navigation experiments demonstrated that the system outperforms an unguided system during real drops. The work done to compare the effectiveness of different navigation strategies in a simulated environment represents the beginning of the next stage in the development of the parachute system. This next stage involves refinement and performance improvements of the existing platform through engineering design in order to advance the technical readiness level of the project.Introduction -- Literature review -- Vertical wind tunnel experiment -- Investigation of navigation strategies -- Conclusions -- Appendix A. Unmanned aerial systems and parachute release mechanisms -- Appendix B. Aerial guidance unit redesig

Laser/optics techniques Interim summary report

Laboratory prototype laser telescope package for deep space communication

Guidance of Nonlinear Nonminimum-Phase Dynamic Systems

The first two years research work has advanced the inversion-based guidance theory for: (1) systems with non-hyperbolic internal dynamics; (2) systems with parameter jumps; (3) systems where a redesign of the output trajectory is desired; and (4) the generation of recovery guidance maneuvers