Samir A. Rawashdeh

Fashion or Technology? A Fashnology Perspective on the Perception and Adoption of Augmented Reality Smart Glasses

Abstract Smart glasses are a new family of technological devices that share several characteristics with conventional eyeglasses. Yet, little is known about how individuals process them. Drawing upon categorization theories and prior research on technology acceptance, the authors conduct two empirical studies to show that (a) smart glasses are perceived as technology but vary in their degree of fashion, (b) the perception of smart glasses determines the factors that explain adoption intention, and (c) a majority of consumers process smart glasses as a combination of fashion and technology (“fashnology”), whereas a smaller number of consumers perceive them exclusively as technology or fashion, respectively.

Nano-Satellite Passive Attitude Stabilization Syste ms Design by Orbital Environment Modeling and Simulation

Passive attitude stabilization techniques such as G ravity Gradient stabilization, Passive Magnetic Stabilization, and Aerodynamic stabilizati on in Low Earth Orbit (LEO) are effective and relatively simple methods to control the attitude of small satellites and provide basic pointing control. The design of such stabiliz ation systems is achievable using a high fidelity simulation of all major environmental effe cts of the desired orbit to study the onorbit behavior and the effectiveness of the stabili ty system in overcoming the disturbance torques. The Attitude Propagator described in this paper was developed to study earthorbiting nano-satellites and includes models for th e orbit parameters, gravity gradient torque, aerodynamic torque, magnetic torque, and magnetic hysteresis material behavior for angular rotation damping. The implementation of the Orbital Environment Simulator is described, followed by analysis and verification of the simulation accuracy using collected on-orbit data of passively stabilized satellites. F inally, the Passive Magnetic Stabilization system of KySat-1, a one-unit CubeSat designed by Kentucky Space, is described in detail with the corresponding simulation results from the Orbital Environment Simulator.

Wearable IMU for Shoulder Injury Prevention in Overhead Sports

Body-worn inertial sensors have enabled motion capture outside of the laboratory setting. In this work, an inertial measurement unit was attached to the upper arm to track and discriminate between shoulder motion gestures in order to help prevent shoulder over-use injuries in athletics through real-time preventative feedback. We present a detection and classification approach that can be used to count the number of times certain motion gestures occur. The application presented involves tracking baseball throws and volleyball serves, which are common overhead movements that can lead to shoulder and elbow overuse injuries. Eleven subjects are recruited to collect training, testing, and randomized validation data, which include throws, serves, and seven other exercises that serve as a large null class of similar movements, which is analogous to a realistic usage scenario and requires a robust estimator.

Image-based attitude propagation for small satellites using RANSAC

This work develops a star-based attitude propagator that uses relative motion of stars in an imagers field of view to infer the motion of a satellite by calculating relative attitude estimates in three degrees of freedom. Algorithms to perform the star detection, correspondence using the random sample consensus (RANSAC), and attitude propagation are presented. The work presented here overviews the approach, describes the developed algorithms, evaluates experimental results, and offers component selection for a CubeSat imaging system.

Development of a modular command and data handling architecture for the KySat-2 CubeSat

KySat-2 is a 1U CubeSat launched on the NASA ELaNa IV mission on November 19, 2013. The Command & Data Handling (C&DH) architecture for KySat-2 leverages aspects of the Space Plug-and Play Avionics (SPA) standard developed by the Air Force Research Laboratory (AFRL) and adapts it to the constraints of the CubeSat form factor. The design eases interfacing commercial-off-the-shelf (COTS) and legacy components in the satellite and also enhances software reusability, with motivation to decrease time-to-orbit and reduce system cost and complexity, while increasing reliability. The KySat-2 CubeSat C&DH architecture utilizes a central processor that carries out mission-specific functionality, command interpretation, and scheduling. Interface processors are dedicated to, and all processors communicate on a shared I2C bus. This distributed processing architecture provides a level of abstraction between the mission-specific functionality and the more general purpose features of satellite subsystems, enabling increased reuse of non-mission specific hardware and software. This paper describes the distributed architecture of the KySat-2 C&DH, as well as the advantages and challenges of the distributed approach.

SOCEM: Sub-Orbital CubeSat Experimental Mission

SOCEM: Sub-Orbital CubeSat Experimental Mission will attempt, for the first time, to eject CubeSats in space from a sub-orbital sounding rocket.1 2 This technology demonstration flight will eject two CubeSats from a standard 17-inch diameter NASA sounding rocket. Two student-designed and student-built CubeSats will be ejected as part of the mission, a 2U CubeSat ADAMASat (Antenna Deployment and Mono-filament Actuator Satellite) developed by Kentucky Space to test CubeSat actuator designs and a 1U CubeSat developed by Cal Poly as a test-bed for PolySat bus technologies. The CubeSats will be ejected perpendicular to the direction of flight without requiring a de-spin maneuver providing the CubeSats with several minutes in space before re-entry and impact in the Atlantic Ocean. The SOCEM flight is scheduled for launch on 21 January 2010. Success in this effort could provide a robust ride-share technology for future NASA sounding rocket missions.

Design of a Stellar Gyroscope for visual attitude propagation for small satellites

Attitude Determination is critical for many CubeSat class satellites. However, the mass, volume, and power constraints of the CubeSat form factor limit the options available to designers. In this work, we are developing a Stellar Gyroscope to generate spacecraft relative attitude estimates in three degrees of freedom without the drift associated with most solid state based gyroscope approaches. A Stellar Gyroscope is a star based attitude propagator that uses relative motion of stars in an imagers field of view. Algorithms to perform the star detection, correspondence, and attitude propagation are presented. The Random Sample Consensus (RANSAC) approach is applied to the correspondence problem to mitigate false-positive and false-negative star detections. This paper overviews the approach, describes the details of the solutions for the challenging aspects of the approach, evaluates experimental results, and offers component selection for a preliminary designs for a CubeSat system.

Thermoelectrical Modeling of Wavelength Effects on Photovoltaic Module Performance—Part II: Parameterization

Intervals of the incident solar spectrum associated with long wavelengths do not contribute to electricity production due to their low energy levels. However, light with such wavelengths partially passes through the module layers, while the remainder is either reflected or absorbed as heat into them. Absorbed heat increases the solar module temperature and reduces its efficiency. In Part I, a thermoelectrical model is proposed in order to study the effects of the individual wavelengths on the photovoltaic (PV) module performance. In this paper, a method to characterize the model is proposed. A case study that shows the extraction and the derivation of all required parameters for the model is presented. The experiments are conducted on a lab-built monocrystalline silicon PV module. An optical model is presented to predict the optical properties of the module layers. It is found that characterizing the model using the proposed parameterization methodology leads to predicted results that are consistent with the experimental measurements.

Wearable motion capture unit for shoulder injury prevention

Body-worn devices have significant potential to improve the health and well-being of many individuals. In this work, wearable inertial sensors are used in order to track and discriminate shoulder motion gestures, without using visual markers or other approaches that constrain the system to a laboratory environment. The device, consisting of a set of orthogonal accelerometers, gyroscopes, and magnetic field sensors, is attached to the persons upper arm to help prevent shoulder over-use injuries in strenuous work and in athletics. The sensor suite is used to track the orientation of the arm as a function of time. We present a detection and classification approach that can be used to evaluate the number of times certain motion gestures occur.

A SPA-1 Enabled Plug-and-Play CubeLab for ISS Payloads.

This paper describes the design and development of a system to provide a Space Plugand-play Avionics (SPA) interface in a CubeLab form-factor to extend the capabilities of the International Space Station (ISS) to interface directly with SPA-1 compliant devices. The CubeLab is a new payload standard for access to the ISS for small, rapid turn-around microgravity experiments. CubeLabs are small (less than 16”x8”x4” and under 10kg) modular payloads that interface with the NanoRacks Platform aboard the ISS, receive power and transfer data using plug-and-Play Universal Serial Bus (USB) standard. The SPA architecture is a modular technology for spacecraft that provides an infrastructure for modular satellite components to reduce the time to orbit and development costs for satellites. The new system described in this paper allows developers to easily operate their SPA-1 based experiments and payloads aboard the ISS. In addition, developers of new SPA-1 devices can rapidly access the microgravity environment of space.