Blade guard for rotary lawn mowers

A blade guard for rotary lawn mowers comprising a plurality of spaced apart elongated members which extend longitudinally in the intended direction of travel of the mower device. The space between the forward ends of the elongated members and the forward end of the mower cowling is open and free from obstructions to permit the grass to be sucked upwardly for cutting by the mower blade. The elongated members have varying lengths to define an effective area substantially the same as the area defined by the unsharpened center portion of the mower blade when rotating so that the sharpened ends of the blade extend outwardly beyond the effective area of the guard means. The guard means is hinged to the mower cowling to permit convenient cleaning of the mower. An ignition interlock means is also connected to the guard.

Rotary tiller slot planter and method for using the same

The rotary tiller slot planter of the present invention comprises a subsoiler shank positioned to engage the soil and make a trench therein. A pair of rotary tiller blades are rotatably mounted on the opposite sides of the sub-soil shank in planes parallel thereto. The center-lines of the rotary tiller wheels are located behind the subsoil shank. Each of the wheels have a plurality of blades extending radially outwardly from the rotational axis thereof and terminating in outer radial ends which engage the soil slightly ahead of the subsoiler shank and adjacent the lateral edges of the trench. A seed tube shank is positioned behind the subsoiler shank and between the tiller wheels. The seed tube shank has a lower end positioned to extend below the soil surface. A seed tube is positioned behind the seed tube shank for depositing seed in the soil. The rotation of the blades on opposite sides of the subsoil shank causes the soil to be mechanically aggregated and aerated and helps prepare a seed bed for the seeds. Also, the rotating tiller blades chop the debris which may be along the trench and throw soil backwards so as to cover the planted seed. Shorter rotary blades on the tiller wheels are shaped to throw debris and the upper one-half inch of soil sideways away from the row.

Sea ice thickness from airborne electromagnetic (EM) induction sounding acquired from fixed-wing aircraft POLAR 5 surveys from several airports in Spitsbergen, Greenland, Canada and Alaska

While summer Arctic sea-ice extent has decreased over the past three decades, it is subject to large interannual and regional variations. Methodological challenges in measuring ice thickness continue to hamper our understanding of the response of the ice-thickness distribution to recent change, limiting the ability to forecast sea-ice change over the next decade. We present results from a 2400 km long pan-Arctic airborne electromagnetic (EM) ice thickness survey in April 2009, the first-ever large-scale EM thickness dataset obtained by fixed-wing aircraft over key regions of old ice in the Arctic Ocean between Svalbard and Alaska. The data provide detailed insight into ice thickness distributions characteristic for the different regions. Comparison with previous EM surveys shows that modal thicknesses of old ice had changed little since 2007, and remained within the expected range of natural variability.

Desarrollo de un datalink con el chip CC1110 de Texas Instruments para UAVs

Se trata de estudiar el comportamiento de un sistema basado en el chip CC1110 de Texas Instruments, para aplicaciones inalámbricas. Los dispositivos basados en este tipo de chips tienen actualmente gran profusión, dada la demanda cada vez mayor de aplicaciones de gestión y control inalámbrico. Por ello, en la primera parte del proyecto se presenta el estado del arte referente a este aspecto, haciendo mención a los sistemas operativos embebidos, FPGAs, etc. También se realiza una introducción sobre la historia de los aviones no tripulados, que son el vehículo elegido para el uso del enlace de datos. En una segunda parte se realiza el estudio del dispositivo mediante una placa de desarrollo, verificando y comprobando mediante el software suministrado, el alcance del mismo. Cabe resaltar en este punto que el control con la placa mencionada se debe hacer mediante programación de bajo nivel (lenguaje C), lo que aporta gran versatilidad a las aplicaciones que se pueden desarrollar. Por ello, en una tercera parte se realiza un programa funcional, basado en necesidades aportadas por la empresa con la que se colabora en el proyecto (INDRA). Este programa es realizado sobre el entorno de Matlab, muy útil para este tipo de aplicaciones, dada su versatilidad y gran capacidad de cálculo con variables. Para terminar, con la realización de dichos programas, se realizan pruebas específicas para cada uno de ellos, realizando pruebas de campo en algunas ocasiones, con vehículos los más similares a los del entorno real en el que se prevé utilizar. Como implementación al programa realizado, se incluye un manual de usuario con un formato muy gráfico, para que la toma de contacto se realice de una manera rápida y sencilla. Para terminar, se plantean líneas futuras de aplicación del sistema, conclusiones, presupuesto y un anexo con los códigos de programación más importantes. Abstract In this document studied the system behavior based on chip CC1110 of Texas Instruments, for wireless applications. These devices currently have profusion. Right the increasing demand for control and management wireless applications. In the first part of project presents the state of art of this aspect, with reference to the embedded systems, FPGAs, etc. It also makes a history introduction of UAVs, which are the vehicle for use data link. In the second part is studied the device through development board, verifying and checking with provided software the scope. The board programming is C language; this gives a good versatility to develop applications. Thus, in third part performing a functionally program, it based on requirements provided by company with which it collaborates, INDRA Company. This program is developed with Matlab, very useful for such applications because of its versatility and ability to use variables. Finally, with the implementation of such programs, specific tests are performed for each of them, field tests are performed in several cases, and vehicles used for this are the most similar to the actual environment plain to use. Like implementing with the program made, includes a graphical user manual, so your understanding is conducted quickly and easily. Ultimately, present future targets for system applications, conclusions, budget and annex of the most important programming codes.

Aeroelastic characteristics of slender wing/bodies with freeplay non-linearities

This article presents a time domain approach to the flutter analysis of a missile-type wing/body configuration with concentrated structural non-linearities. The missile wing is considered fully movable and its rotation angle contains the structural freeplay-type non-linearity. Although a general formulation for flexible configurations is developed, only two rigid degrees of freedom are taken into account for the results: pitching of the whole wing/body configuration and wing rotation angle around its hinge. An unsteady aerodynamic model based on the slender-body approach is used to calculate aerodynamic generalized forces. Limit-cycle oscillations and chaotic motion below the flutter speed are observed in this study.

Experimental investigation on box-wing configuration for UAS

The range for airframe configurations available for UAS is as diverse as those used for manned aircraft and more since the commercial risk in trying unorthodox solutions is less for the UAS manufacturer. This is principally because the UAS airframes are usually much smaller than the manned aircraft and operators are less likely to have a bias against unconventional configurations. One of these unconventional configurations is the box-wing, which is an unconventional solution for the design of the new UAS generation. The existence of two wings separated in different planes that are, however, significantly close together, means that the aerodynamic analysis by theoretical or computational methods is a difficult task, due to the considerable interference existing. Considering the fact that the flight of most UAS takes place at low Reynolds numbers, it is necessary to study the aerodynamics of the box wing configuration by testing different models in a wind tunnel to be able to obtain reasonable results. In the present work, the study is enhanced by varying not only the sweepback angles of the two wings, but also their position along the models’ fuselage. Certain models have shown being more efficient than others, pointing out that certain relative positions of wing exists that can improve the aerodynamics efficiency of the box wing configuration.

A hierarchical strategy for real-time tracking on-board UAVs

In this paper, we present a real-time tracking strategy based on direct methods for tracking tasks on-board UAVs, that is able to overcome problems posed by the challenging conditions of the task: e.g. constant vibrations, fast 3D changes, and limited capacity on-board. The vast majority of approaches make use of feature-based methods to track objects. Nonetheless, in this paper we show that although some of these feature-based solutions are faster, direct methods can be more robust under fast 3D motions (fast changes in position), some changes in appearance, constant vibrations (without requiring any specific hardware or software for video stabilization), and situations where part of the object to track is out the field of view of the camera. The performance of the proposed strategy is evaluated with images from real-flight tests using different evaluation mechanisms (e.g. accurate position estimation using a Vicon sytem). Results show that our tracking strategy performs better than well known feature-based algorithms and well known configurations of direct methods, and that the recovered data is robust enough for vision-in-the-loop tasks.

Arquitectura cognitiva híbrida para la navegación autónoma de UAVs mediante mapas topológicos visuales

El objetivo fundamental de la presente tesis doctoral es el diseño de una arquitectura cognitiva, que pueda ser empleada para la navegación autónoma de vehículos aéreos no tripulados conocidos como UAV (Unmanned Aerial Vehicle). Dicha arquitectura cognitiva se apoya en la definición de una librería de comportamientos, que aportarán la inteligencia necesaria al UAV para alcanzar los objetivos establecidos, en base a la información sensorial recopilada del entorno de operación. La navegación autónoma del UAV se apoyará en la utilización de un mapa topológico visual, consistente en la definición de un grafo que engloba mediante nodos los diferentes landmarks ubicados en el entorno, y que le servirán al UAV de guía para alcanzar su objetivo. Los arcos establecidos entre los nodos del mapa topológico, le proporcionarán de la información necesaria para establecer el rumbo más adecuado para alcanzar el siguiente landmark a visitar, siguiendo siempre una secuencia lógica de navegación, basada en la distancia entre un determinado landmark con respecto al objetivo final ó landmark destino. La arquitectura define un mecanismo híbrido de control, el cual puede conmutar entre dos diferentes modos de navegación. El primero es el denominado como Search Mode, el cual se activará cuando el UAV se encuentre en un estado desconocido dentro del entorno, para lo cual hará uso de cálculos basado en la entropía para la búsqueda de posibles landmarks. Se empleará como estrategia novedosa la idea de que la entropía de una imagen tiene una correlación directa con respecto a la probabilidad de que dicha imagen contenga uno ó varios landmarks. De esta forma, la estrategia para la búsqueda de nuevos landmarks en el entorno, se basará en un proceso continuo de maximización de la entropía. Si por el contrario el UAV identifica la existencia de un posible landmark entre los definidos en su mapa topológico, se considerará que está sobre un estado conocido, por lo que se conmutará al segundo modo de navegación denominado como Homing Mode, el cual se encargará de calcular señales de control para la aproximación del UAV al landmark localizado. Éste último modo implementa un control dual basado en dos tipos de controladores (FeedForward/FeedBack) que mediante su combinación, aportarán al UAV señales de control cada vez más óptimas, además de llevar a cabo un entrenamiento continuo y en tiempo real. Para cumplir con los requisitos de ejecución y aprendizaje en tiempo real de la arquitectura, se han tomado como principales referencias dos paradigmas empleados en diferentes estudios dentro del área de la robótica, como son el paradigma de robots de desarrollo (developmental robots) basado en un aprendizaje del robot en tiempo real y de forma adaptativa con su entorno, así como del paradigma de modelos internos (internal models) basado en los resultados obtenidos a partir de estudios neurocientíficos del cerebelo humano; dicho modelo interno sirve de base para la construcción del control dual de la arquitectura. Se presentarán los detalles de diseño e implementación de los diferentes módulos que componen la arquitectura cognitiva híbrida, y posteriormente, los diferentes resultados obtenidos a partir de las pruebas experimentales ejecutadas, empleando como UAV la plataforma robótica aérea de AR.Drone. Como resultado final se ha obtenido una validación completa de la arquitectura cognitiva híbrida objetivo de la tesis, cumplimento con la totalidad de requisitos especificados y garantizando su viabilidad como aplicación operativa en el mundo real. Finalmente, se muestran las distintas conclusiones a las cuales se ha llegado a partir de los resultados experimentales, y se presentan las diferentes líneas de investigación futuras que podrán ser ejecutadas.

A Hierarchical Tracking Strategy for Vision-Based Applications On-Board UAVs

In this paper, we apply a hierarchical tracking strategy of planar objects (or that can be assumed to be planar) that is based on direct methods for vision-based applications on-board UAVs. The use of this tracking strategy allows to achieve the tasks at real-time frame rates and to overcome problems posed by the challenging conditions of the tasks: e.g. constant vibrations, fast 3D changes, or limited capacity on-board. The vast majority of approaches make use of feature-based methods to track objects. Nonetheless, in this paper we show that although some of these feature-based solutions are faster, direct methods can be more robust under fast 3D motions (fast changes in position), some changes in appearance, constant vibrations (without requiring any specific hardware or software for video stabilization), and situations in which part of the object to track is outside of the field of view of the camera. The performance of the proposed tracking strategy on-board UAVs is evaluated with images from realflight tests using manually-generated ground truth information, accurate position estimation using a Vicon system, and also with simulated data from a simulation environment. Results show that the hierarchical tracking strategy performs better than wellknown feature-based algorithms and well-known configurations of direct methods, and that its performance is robust enough for vision-in-the-loop tasks, e.g. for vision-based landing tasks.

Aerodynamic study of a blended wing body, comparison with a conventional transport airplane.

Blended-wing-body (BWB) aircraft are being studied with interest and effort to improve economic efficiency and to overcome operational and infrastructure related problems associated to the increasing size of conventional transport airplanes. The objective of the research reported here is to assess the aerodynamic feasibility and operational efficiency of a great size, blended wing body layout, a configuration which has many advantages. To this end, the conceptual aerodynamic design process of an 800 seat BWB has been done completed with a comparison of performance and operational issues with last generation of conventional very large aircraft. The results are greatly encouraging and predict about 20 percent increase in transport productivity efficiency, without the burden of new or aggravated safety or operational problems.

Cancellation zone in supersonic lifting wing theory

BASING their work on a linear theory, Evvard1 and Krasilshchikova2'3 independently developed an expression that yields the perturbation generated by a thiri lifting wing of arbitrary planform flying at supersonic speed on a point placed on the wing plane inside its planform,1 or both on and above the wing plane.2 This point must be influenced by two leading edges, one supersonic and the other partially subsonic. Although these authors followed different approaches, their methods concur in showing the existence of a perfectly defined cancellation zone. In this Note, the Evvard approach is generalized to the case solved by Krasilshchikova. Circumventing the latter's lengthy and somewhat complex approach, Evvard's simple method seems to be useful at least for educational purposes.