DESIGN OF A CANARD-WING UAV

In this project, we intend to design a Canard wing-based Unmanned Aerial Vehicle (UAV), which can carry a wide range of missions, providing capabilities to handle our challenges with sophisticated care. Canard-based UAV is the latest trend in aviation technology designed for the use case of providing better maneuverability, which in result gives the UAV new capabilities, such as increased time for data gathering, transferring, and autonomous behavior. The basic disciplines like Aerodynamics, Engineering design, Flight dynamics, Propulsion, and Performance are carried out during the UAV designing process. The proposed methodology applied in this project is weight estimation, initial sizing, aerofoil and wing geometry, fuselage sizing, tail sizing, T/W ratio, aerodynamics, and performance analysis. The design of Canard Based UAV leads to a deeper understanding of the trade-off studies of the UAV and is demonstrated by optimizing for designed missions like surveillance. A drafted sketch is presented at the end of the design phase featuring the selected configurations of major components.

Design and Analysis of VTOL Operated Intercity Electrical Vehicle for Urban Air Mobility

This paper discusses the conceptual design of an intercity electrical vertical take-off-and-landing aircraft. A literature survey of existing eVTOL aircrafts, configuration selection, initial sizing, weight estimation, modelling and analysis was conducted. The present intercity eVTOL aircraft has the capability to carry four passengers along with one pilot for a distance of 500 km. Two specific aircraft modes, such as air-taxi and air-cargo mode, are considered in the present design. Market entry is predicted before 2031. Subsequently, innovative technologies are incorporated into the design. The present design features an aerodynamically shaped fuselage, tapered wing and a V-tail design. It can carry a nominal payload of 500 kg to a maximum range of 500 km at a cruise speed of Mach 0.168. The present eVTOL is comprised of a 5 m-long fuselage and an 11 m wingspan. It utilizes six tilt-rotor propeller engines. The maximum take-off weight and empty weight are 1755 kg and 1255 kg, respectively. The unit price is expected to be between USD 14.83 and 17.36 million. This aircraft has an aesthetically pleasing, intelligent and feasible design.

Regression Equations for Weight Estimation in Paediatric Resuscitation

Background: Weight estimation is critical in paediatric resuscitation, as stopping to weigh a child could influence their survival. Weight estimation methods used in New Zealand (NZ) are not accurate for the population, increasing the complexity of prescribing medication and selecting equipment. Aim: Develop regression equations (RE) to predict the weight of NZ children based on height, sex, age and ethnicity to be deployed in a mobile application (Weight Estimation Without Waiting). Methods: The RE was derived from retrospective regression modelling of a large existing dataset. Data were presented using descriptive statistics and calculation of means, limits of agreement and the proportion of weight estimates within a percentage of actual weight. Conclusion: The RE developed in this study outperformed existing age-based weight estimation methods while providing a method to ensure that weight estimation techniques evolve with NZ children.

LIGHTSHIP WEIGHT ESTIMATION OF WIND FARM SUPPORT VESSELS AT THE INITIAL DESIGN STAGE

The issue of the determination of lightship weight estimates of wind farm support vessels (WFSV) is considered. The algorithm of determination of components of the lightship weight is suggested. The hull weight of the ships suggested to be calculated through the surface area of the principal structural elements using the parametrical model. The formula for calculation of weight and volume of the superstructures was obtained by making the 3D model of the superstructures of the most widespread projects of WFSV. Using the statistical data processing the dependences were obtained for the determination of engine, gearbox and waterjet weights, which are used in WFSV. The results of the comparative analysis of the lightship weight of WFSV are given.

Depth Image Selection Based on Posture for Calf Body Weight Estimation

We are developing a system to estimate body weight using calf depth images taken in a loose barn. For this purpose, depth images should be taken from the side, without calves overlapping and without their backs bent. However, most of the depth images that are taken successively and automatically do not satisfy these conditions. Therefore, we need to select only the depth images that match these conditions, as to take many images as possible. The existing method assumes that a calf standing sideways and upright in front of cameras is in a suitable pose. However, since such cases rarely occur, not many images were selected. This paper proposes a new depth image-selection method, focusing on whether a calf is sideways, and the back is not bent, regardless of whether the calf is still or walking. First, depth images including only a single calf are extracted. The calf was identified using radio frequency identification (RFID) when its depth image was taken. Then, the calf area was extracted by background subtraction and contour detection with a depth image. Finally, to judge the usable depth images, we detected and evaluated the calf’s posture, such as the angle of the calf to the camera and the slope of the dorsal line. We used the mean absolute percentage error (MAPE) to assess the efficiency of our method. As two times the number of depth images were extracted, our method achieved an MAPE of 12.45%, while the existing method achieved an MAPE of 13.87%. From this result, we have confirmed that our method makes body weight estimation more accurate.

Estimation of Hemi-Abdominal-Based Free Flap Weight Using Two Computed Tomography-Derived Measurements

Background Accurate flap weight estimation is crucial for preoperative planning in microsurgical breast reconstruction; however, current flap weight estimation methods are time consuming. It was our objective to develop a parsimonious and accurate formula for the estimation of abdominal-based free flap weight. Methods Patients who underwent hemi-abdominal-based free tissue transfer for breast reconstruction at a single institution were retrospectively reviewed. Subcutaneous tissue thicknesses were measured on axial computed tomography angiograms at several predetermined points. Multivariable linear regression was used to generate the parsimonious flap weight estimation model. Split-sample validation was used to for internal validation. Results A total of 132 patients (196 flaps) were analyzed, with a mean body mass index of 31.2 ± 4.0 kg/m2 (range: 22.6–40.7). The mean intraoperative flap weight was 990 ± 344 g (range: 368–2,808). The full predictive model (R 2 = 0.68) estimated flap weight using the Eq. 91.3x + 36.4y + 6.2z – 1030.0, where x is subcutaneous tissue thickness (cm) 5 cm lateral to midline at the level of the anterior superior iliac spine (ASIS), y is distance (cm) between the skin overlying each ASIS, and z is patient weight (kg). Two-thirds split-sample validation was performed using 131 flaps to build a model and the remaining 65 flaps for validation. Upon validation, we observed a median percent error of 10.2% (interquartile range [IQR]: 4.5–18.5) and a median absolute error of 108.6 g (IQR: 45.9–170.7). Conclusion We developed and internally validated a simple and accurate formula for the preoperative estimation of hemi-abdominal-based free flap weight for breast reconstruction.