A system is designed to deploy and support a tethered ground robot from an autonomous helicopter. A winch is designed and built. Electrical hardware for power distribution and control are designed. Several applied controls problems are investigated. A control architecture is established and low level controllers are designed to meet the demands of two higher level algorithms. A tether tension controller is designed to avoid the danger of excess slack in the tether interfering with the robot's mobility. A payload sway damping controller is investigated and simulated. Its is shown to be effective in damping dangerous payload oscillations by modulating the vertical manipulation of the winch during hoisting. Future design recommendations are given regarding improvements for a second design iteration. / Master of Science

A tension control algorithm for the deployment of a unmanned ground vehicle from an autonomous helicopter is designed and tested in this thesis. The physical hardware which the controller will run on is detailed. The plant model and underlying controllers are derived and modeled. The tension controller algorithm is selected, derived, and modeled. The parameters of the tension controller are chosen and simulations are run with the chosen parameters. The tension control algorithm is run on the physical hardware, successfully demonstrating tension control on a ground vehicle. Robustness simulations are run for a change in the radius of the spool and the length of the tether. Lastly, Future work is outlined on several paths to move forward with the tension controller. / Master of Science

Unmanned aerial vehicles and unmanned ground vehicles, or UAVs and UGVs respectively, currently perform a large variety of missions usually centered around reconnaissance. Because the platforms may vary for a particular type of mission--everything from small unmanned airplanes and remote control vehicles to large vehicles such as the Yamaha R-MAX helicopter and Hummer--flight and navigation controllers must be changed to allow proper control of the selected platform. Currently, controllers are designed and tested in MATLAB/SIMULINK, but then rewritten in C or Assembly for a specific target platform. When designing controllers in a programming language, changes are often tedious, so producing a working controller takes considerable time. MATLAB/SIMULINK provides a GUI interface and SIMULINK provides excellent testing capabilities, so changes may be quick and easy. However, no automated method for converting a simple controller, such as a PID for example, from MATLAB to implementation on a microcontroller has been presented in literature. To implement current in-house controllers designed in MATLAB/SIMULINK, a system consisting of Real-Time Workshop and a C compiler has been used to produce assembly code for a target microcontroller. To aid in verification of the controllers and C code produced by Real-Time Workshop targeted toward aerial platforms, an interface for the controllers in SIMULINK and a flight simulator (X-Plane) has been created. Thus the overall system allows for rapid changes and implementation on a variety of platforms as well as plug-in/plug-out capabilities in the field for diverse missions. Functionality and diversity of the system is demonstrated through testing of PID VTOL controllers in SIMULINK with X-Plane as well as implementation of UGV controllers onboard a small radio controlled truck.

Approved for public release; distribution is unlimited. / U.S. military and civilian vessels are critically vulnerable to asymmetric threats in littoral environments. Common asymmetric weapons such as Anti-Ship Cruise Missiles (ASCM), Low Slow Flying (LSF) aircraft and Fast Attack Craft (FAC) / Fast Inshore Attack Craft (FIAC) threaten U.S. strategic goals and can produce unacceptable losses of men and material. The SEA-18B team presents an operational concept for a family of Unmanned Surface Vessels USV) capable of defending ships from asymmetric swarm attacks. This USV, the Tailorable Remote Unmanned Combat Craft (TRUCC), can operate in concert with the next generation of capital surface vessels to combat this critical threat with maximum efficiency. Critical performance criteria of the TRUCC family were determined through agent-based simulation of a Straits of Hormuz Design Reference Mission. Additional models addressed ship synthesis and operational availability. A Technology and Capability Roadmap outlines areas of interest for investment and development of the next-generation USV. Interim technology and capability milestones in the Roadmap facilitate incremental USV operational capabilities for missions such as logistics, decoy operations and Mine Warfare. The TRUCC operational concept fills a critical vulnerability gap. Its employment will reduce combat risk to our most valuable maritime assets: our ships and our Sailors.

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The robotics field has grown in recent years to a point where unmanned systems are no longer limited by their capabilities. As such, the mission profiles for unmanned systems are becoming more and more complicated, and a demand has risen for the deployment of unmanned systems into the most complex of environments. Additionally, the objectives for unmanned systems are once more complicated by the necessity for beyond line of sight teleoperation, and in some cases complete vehicle autonomy. Such systems require adequate sensory devices for appropriate situational awareness. Additionally, a large majority of what is currently being done with unmanned systems requires visual data acquisition. A stereo vision system is ideal for such missions as it doubles as both an image acquisition device, and a range finding device. The 2D images captured with a stereo vision system can be mapped to three dimensional point clouds with reference to the optic center of one of the stereo cameras. While stand alone commercial stereo vision systems are capable of doing just that, the GPS/INS aided stereo vision system also has integrated 3-axis accelerometers, 3-axis gyros, 3-axis magnetometer, and GPS receiver allowing for the measurement of the system's position and orientation in global coordinates. This capability provides the potential to geo-reference the 3D data captured with the stereo camera. The GPS/INS aided stereo vision system integrates a combination of commercial and in-house developed devices. The total system includes a Point Grey Research Bumblebee stereovision camera, a Versalogic PC104 computer, a PCB designed for sensor acquisition and power considerations, and a self contained battery. The entire system is all contained within a 9.5â x 5â x 6.5â aluminum enclosure and weighs approximately 6 lbs. The system is also accompanied with a graphical user interface which displays the geo-referenced data within a 3D virtual environment providing adequate sensor feedback for a teleoperated unmanned vehicle. This thesis details the design and implementation of the hardware and software included within this system as well as the results of operation. / Master of Science

The design of unmanned material collection systems requires a great deal of foresight and innovative design on the engineer's part in order to produce solutions to problems operators may encounter in the field. In this thesis, the development of a particulate collection system for use onboard a lightweight, helicopter deployable ground robot is presented. The Unmanned Systems Laboratory at Virginia Tech is developing a ground sampling robot to be carried in the payload pod of a Yamaha RMAX unmanned aerial vehicle. The robot's ultimate objective is to collect material samples from a hazardous environment. The pneumatic system presented here is a novel design developed to collect particulate without draining the resources of the robot. Vacuum samplers have been developed in the past, but they are large and cumbersome and require large amounts of electrical energy to operate. The pneumatic particulate collection system utilizes the kinetic energy from the release of compressed air to transport the particulate to a collection chamber. Consideration is given to the drop in pressure of the air supply tank as it empties, and a feasible air supply tank design is presented. Two forms of particulate collection are investigated experimentally: jet impingement and particle entrainment (i.e. steep attack angle and parallel flow). Turbulent, free jet characteristics and critical velocities of particles are studied. Ultimately, a final design is presented that effectively collects particulate material from the top 5/8" layer of both thick and thin particle beds. / Master of Science

Conventional stereo vision systems rely on two spatially fixed cameras to gather depth information about a scene. The cameras typically have a fixed distance between them, known as the baseline. As the baseline increases, the estimated 3D information becomes more accurate, which makes it advantageous to have as large a baseline as possible. However, large baselines have problems whenever objects approach the cameras. The objects begin to leave the field of view of the cameras, making it impossible to determine where they are located in 3D space. This becomes especially important if an object of interest must be actuated upon and is approached by a vehicle. In an attempt to overcome this limitation, this thesis introduces a variable baseline stereo system that can adjust its baseline automatically based on the location of an object of interest. This allows accurate depth information to be gathered when an object is both near and far. The system was designed to operate under, and automatically move to a large range of different baselines. This thesis presents the mechanical design of the stereo boom. This is followed by a derivation of a control scheme that adjusts the baseline based on an estimate object location, which is gathered from stereo vision. This algorithm ensures that a certain incident angle on an object of interest is never surpassed. This maximum angle is determined by where a stereo correspondence algorithm, Semi-Global Block Matching, fails to create full reconstructions. / Master of Science

Unmanned vehicles, both ground and aerial, have become prevalent in recent years. The research community has different needs than the industrial community when designing a finalized unmanned system since the vehicle, the sensors and the control design are dynamic and change frequently as new ideas are developed and implemented. Current autopilot hardware, which is available as on-the-market products and proposed in research, is sufficient for unmanned systems design. However, this equipment falls short of being able to accommodate the needs of those in the research community who must be able to quickly implement new ideas on a flexible platform. The contribution of this research is the realization of a hardware platform, which provides for rapid implementation of newly developed theory. Rapid implementation is gained by providing for software development from within the Simulink environment and utilizing previously unrealized flexibility in sensor selection. In addition to the development of the hardware platform, research was performed within Simulink's System Generator environment in order to complement the hardware. The software produced consists of a user template that integrates to the selected hardware. The template creates a user friendly environment, which provides the end user the capability to develop software algorithms from within the Simulink environment. This capability facilitates the final step of full hardware implementation. The major novelty of the research was the overall FPGA based autopilot design. The approach provided flexibility, functionality and generality. The approach is also suitable for and applicable to the design of multiple platforms. This research yielded a first time approach to the development of an unmanned systems autopilot platform by utilizing: -Development of programmable voltage level digital Input/Output (I/O), ports, -Utilization of Field Programmable Analog Arrays (FPAA), -Hardware capabilities to allow for integration with full computer systems, -A full Field Programmable Gate Array (FPGA), implementation, -Full integration of the hardware within Simulink's System Generator Toolbox

Future spacecraft missions are trending towards the use of distributed systems or fractionated spacecraft. Initiatives such as DARPA's System F6 are encouraging the satellite community to explore the realm of collaborative spacecraft teams in order to achieve lower cost, lower risk, and greater data value over the conventional monoliths in LEO today. Extensive research has been and is being conducted indicating the advantages of distributed spacecraft systems in terms of both capability and cost. Enabling collaborative behaviors among teams or formations of pico-satellites requires technology development in several subsystem areas including attitude determination and control subsystems, orbit determination and maintenance capabilities, as well as a means to maintain accurate knowledge of team members' position and attitude. All of these technology developments desire improvements (more specifically, decreases) in mass and power requirements in order to fit on pico-satellite platforms such as the CubeSat. In this thesis a solution for the last technology development area aforementioned is presented. Accurate knowledge of each spacecraft's state in a formation, beyond improving collision avoidance, provides a means to best schedule sensor data gathering, thereby increasing power budget efficiency. Our solution is composed of multiple software and hardware components. First, finely-tuned flight system software for the maintaining of state knowledge through equations of motion propagation is developed. Additional software, including an extended Kalman filter implementation, and commercially available hardware components provide a means for on-board determination of both orbit and attitude. Lastly, an inter-satellite communication message structure and protocol enable the updating of position and attitude, as required, among team members. This messaging structure additionally provides a means for payload sensor and telemetry data sharing. In order to satisfy the needs of many different missions, the software has the flexibility to vary the limits of accuracy on the knowledge of team member position, velocity, and attitude. Such flexibility provides power savings for simpler applications while still enabling missions with the need of finer accuracy knowledge of the distributed team's state. Simulation results are presented indicating the accuracy and efficiency of formation structure knowledge through incorporation of the described solution. More importantly, results indicate the collaborative module's ability to maintain formation knowledge within bounds prescribed by a user. Simulation has included hardware-in-the-loop setups utilizing an S-band transceiver. Two "satellites" (computers setup with S-band transceivers and running the software components of the collaborative module) are provided GPS inputs comparable to the outputs provided from commercial hardware; this partial hardware-in-the-loop setup demonstrates the overall capabilities of the collaborative module. Details on each component of the module are provided. Although the module is designed with the 3U CubeSat framework as the initial demonstration platform, it is easily extendable onto other small satellite platforms. By using this collaborative module as a base, future work can build upon it with attitude control, orbit or formation control, and additional capabilities with the end goal of achieving autonomous clusters of small spacecraft.