Accessible Vehicle for Kids

The purpose of this document is to outline the process of developing a Go Baby Go vehicle for use by children with disabilities who experience limited or delayed mobility. The purpose of the project is to adapt the Wild Thing, a 12V commercially available ride-on toy car, so that young children with limited mobility can have similar opportunities to independently and actively explore their world for participation, play, learning, and engagement like their same-aged peers. The motivation for undertaking this project is to create a safe and universally designed form of active mobility for children who do not have access to a power wheelchair due to the lack of availability of appropriate products and funding sources for children with disabilities. The original design of the Wild Thing has two joysticks which can be moved by pushing the joysticks either both forward to go forward, both backwards to go backwards and one forward and one backwards in order to spin left or right. Because of this original design, children with limited mobility could have a difficult time navigating the Wild Thing platform. In order to meet this need, the vehicle will be redesigned to support varying options to control the vehicle. These include a single joystick, head array buttons, or hand-pushed buttons. Dependent on the child’s needs, these options can be chosen from, and implemented as the user sees fit. An app will also be utilized that allows control of the vehicle through the use of directional buttons and an emergency stop button. The app will also have the ability to log the usage data of the vehicle. This document contains the design aspects and process of this project

Discrete Concealed Device Table

How can people hide devices in their homes without being obvious with its location? People use safes to hide devices but intruders will know immediately that’s where things are held. It’s a common issue that people are having their safes stolen or broken into. To answer this question, a device was created to conceal devices in plain sight without being noticed. It’s common to have a coffee table in ones living room. Combining the problem with this knowledge, a discrete concealed device table was created. The table looks normal to the naked eye, meaning one cannot tell that the table opens. Inside the table are manufactured parts that hold different sized devices. The manufactured parts are engineered to lock and hold in place, but also have the ability for quick and easy access. The table has a lock located in the inside, one can open the table by sliding a magnetic key card over the locks location. Doing so the table will freely open, revealing one’s hidden devices. The device had a minimum force of 5 lbs and a minimum time of 5 seconds. The test revealed a force of 5 lbs and 7 seconds was required to open the tables top. This was due to having the devices being held on the inside of the tables lid. The second test is the force and time to remove a device from a holder. The requirement was under 10 lbs and 10 seconds. The force revealed was 8lbs and 5 seconds

Analysis and design of optimized truncated scarfed nozzles subject to external flow effects

Rao's method for computing optimum thrust nozzles is modified to study the effects of external flow on the performance of a class of exhaust nozzles. Members of this class are termed scarfed nozzles. These are two-dimensional, nonsymmetric nozzles with a flat lower wall. The lower wall (the cowl) is truncated in order to save weight. Results from a parametric investigation are presented to show the effects of the external flowfield on performance

Analysis and Optimization of Truncated Scarf Nozzles Subject to External Flow Conditions

Results of a calculation of an optimized truncated scarfed nozzle were compared. The truncated scarfed nozzle was designed for an exit Mach number of 6.0, i.e., the Mach number at the last nozzle characteristic is 6.0, with an external flow Mach number of 5.0. The nozzle was designed by the Rao method for optimum thrust nozzles modified for 2-D flow and truncated scarfed nozzle applications. This design was analyzed using a shock-fitting method for 2-D supersonic flows. Excellent agreement was achieved between the design and analysis. Truncation of the lower nozzle wall (cowl) revealed that there is an optimum length for truncating the cowl without degrading the nozzle performance. Truncation of the nozzle cowl past this optimal length should be analyzed in trade-off studies for thrust loss versus gross vehicle weight. Plots of the oblique shock wave equations were also identified which will allow computation of slip line angle, dynamic pressure coefficient, or ambient Mach number for various specific heat ratios

Experimental evaluation of two turning vane designs for fan drive corner of 0.1-scale model of NASA Lewis Research Center's proposed altitude wind tunnel

Two turning vane designs were experimentally evaluated for corner 2 of a 0.1 scale model of the NASA Lewis Research Center's proposed Altitude Wind Tunnel (AWT). Corner 2 contained a simulated shaft fairing for a fan drive system to be located downstream of the corner. The corner was tested with a bellmouth inlet followed by a 0.1 scale model of the crossleg diffuser designed to connect corners 1 and 2 of the AWT. Vane A was a controlled-diffusion airfoil shape; vane B was a circular-arc airfoil shape. The A vanes were tested in several arrangements which included the resetting of the vane angle by -5 degrees or the removal of the outer vane. The lowest total pressure loss for vane A configuration was obtained at the negative reset angle. The loss coefficient increased slightly with the Mach number, ranging from 0.165 to 0.175 with a loss coefficient of 0.170 at the inlet design Mach number of 0.24. Removal of the outer vane did not alter the loss. Vane B loss coefficients were essentially the same as those for the reset vane A configurations. The crossleg diffuser loss coefficient was 0.018 at the inlet design Mach number of 0.33

Comparison of analytical and experimental performance of a wind-tunnel diffuser section

Wind tunnel diffuser performance is evaluated by comparing experimental data with analytical results predicted by an one-dimensional integration procedure with skin friction coefficient, a two-dimensional interactive boundary layer procedure for analyzing conical diffusers, and a two-dimensional, integral, compressible laminar and turbulent boundary layer code. Pressure, temperature, and velocity data for a 3.25 deg equivalent cone half-angle diffuser (37.3 in., 94.742 cm outlet diameter) was obtained from the one-tenth scale Altitude Wind Tunnel modeling program at the NASA Lewis Research Center. The comparison is performed at Mach numbers of 0.162 (Re = 3.097x19(6)), 0.326 (Re = 6.2737x19(6)), and 0.363 (Re = 7.0129x10(6)). The Reynolds numbers are all based on an inlet diffuser diameter of 32.4 in., 82.296 cm, and reasonable quantitative agreement was obtained between the experimental data and computational codes

Detailed flow surveys of turning vanes designed for a 0.1-scale model of NASA Lewis Research Center's proposed altitude wind tunnel

Detailed flow surveys downstream of the corner turning vanes and downstream of the fan inlet guide vanes have been obtained in a 0.1-scale model of the NASA Lewis Research Center's proposed Altitude Wind Tunnel. Two turning vane designs were evaluated in both corners 1 and 2 (the corners between the test section and the drive fan). Vane A was a controlled-diffusion airfoil and vane B was a circular-arc airfoil. At given flows the turning vane wakes were surveyed to determine the vane pressure losses. For both corners the vane A turning vane configuration gave lower losses than the vane B configuration in the regions where the flow regime should be representative of two-dimensional flow. For both vane sets the vane loss coefficient increased rapidly near the walls

The Impact of International Drug Policy on Access to Controlled Medicines: Spanish

As member states of the United Nations take stock of the drug control system, a number of debates have emerged among governments about how to balance international drug laws with human rights, public health, alternatives to incarceration, and experimentation with regulation. This series intends to provide a primer on why governments must not turn a blind eye to pressing human rights and public health impacts of current drug policies.Every year, tens of millions of people suffer disease and pain because they lack access to controlled medicines—that is, medicines of which the distribution and use is regulated under the international drug conventions or national drug-control law. The availability of controlled medicines is limited by the persistence of myths, restrictive regulations, insufficient investment in the training of health professionals—resulting in weak understanding of pain relief and drug dependence—and related failure of supply and distribution systems.Governments and civil society should use the UN General Assembly Special Session on Drugs in April 2016 to highlight the negative impact of overregulation, and misunderstanding of drug dependence on access to controlled medicines, and should seek commitment to concrete action to address imbalance in the system. This report outlines the significant impact the international drug conventions have on access to controlled medicines, and sets out some recommendations for a meaningful debate at the United Nations General Assembly Special Session (UNGASS) and beyond

Experimental Evaluation of Turning Vane Designs for High-speed and Coupled Fan-drive Corners of 0.1-scale Model of NASA Lewis Research Center's Proposed Altitude Wind Tunnel

Two turning vane designs were experimentally evaluated for the fan-drive corner (corner 2) coupled to an upstream diffuser and the high-speed corner (corner 1) of the 0.1 scale model of NASA Lewis Research Center's proposed Altitude Wind Tunnel. For corner 2 both a controlled-diffusion vane design (vane A4) and a circular-arc vane design (vane B) were studied. The corner 2 total pressure loss coefficient was about 0.12 with either vane design. This was about 25 percent less loss than when corner 2 was tested alone. Although the vane A4 design has the advantage of 20 percent fewer vanes than the vane B design, its vane shape is more complex. The effects of simulated inlet flow distortion on the overall losses for corner 1 or 2 were small