Search results

This study aims to a launchable design has been made to prevent wasted time in time-critical areas, and increase the efficiency of the unmanned aerial vehicle (UAV). In this way, a UAV can reach the mission height quickly.

A unique launchable UAV and launcher mechanism have been designed. The launchable UAV will be folded into the launcher mechanism and will automatically start flight after launch. The study includes mathematical calculations, 3D designs steps and produced UAV tests for the designed UAV. The launcher mechanism was designed in accordance with the tests for the UAV, and appropriate choices were made for the altitude and launch acceleration required by the UAV. According to the calculations, material selection and production were made.

In the tests, the climbing time was reduced by 1 s compared with the existing UAVs. With the launch, it enabled it to reach the altitude quickly and silently. In addition, because the launch energy was provided externally, it provided an advantage for the flight time.

A rotary-wing UAV with a launch mechanism and a fast launch was designed and prototyped. The maximum climb speed of the designed drone is 6.52 m/s. Frame arm length is 9.2 cm, propeller diameter is 15.24 cm and hover flight time is 7.2 m.

The UAV design can be launched. Design, calculation and experimental studies have been carried out for rapid take-off of the rotary wing UAV. The parts used in the UAV are originally produced. It is not a commercial product.

Amongst all classes of unmanned aircraft system (UAS), the rise of the Mini UAS class is the most dominant. Mini UASs are field-deployable systems and hence are not expected to operate from a runway. Therefore, the operating terrain plays an important role in the deployment and employment of the Mini UAS. However, there is limited published work in this area. The impact of terrain is more critical for military applications than civilian applications. The purpose of this paper is to explore the implications of various types of terrain on the employment and deployment of Mini UAS.

This paper explores the implications of various types of terrain on the employment and deployment of Mini UAS.

Mini UAS with field deployable requirements is often launched within the tactical battle area in case of military applications or in close proximity to the intended target area for civilian applications. Due to the size and weight of the Mini UAS, launch and recovery becomes an important factor to be considered. Rotary wing or fixed-wing vertical take-off and landing configuration UAS overcomes the limitations of Mini UAS and hence it is the preferred option. Impact of the terrain is significantly higher for military applications as compared to civil applications. Mountain terrain is the most challenging for Mini UAS operations.

This paper will help the designers configure the UAS as per the operating terrain.

Terrain affects the deployment and employment of Mini UAS and the capabilities of the system with respect to terrain in which it is expected to operate must be considered during the design of a Mini UAS. The paper will help the designers configure the UAS as per the operating terrain.

This paper aims to present numerical simulations for a series of flight processes for the postlaunching stage of the “balloon-borne UAV system.” It includes the balloon further ascent motion after airborne launching. In terms of unmanned aerial vehicles (UAVs), the tailspin state and the charge-out process with an anti-tailspin parachute-assisted suspending are analyzed. Then, the authors conduct trajectory optimization simulations for the long-distance gliding process.

The balloon kinematics model and the parachute Kane multibody dynamic model are established. Using steady-state tailspin to reduced-order analysis and achieving change-out simulation by parachute suspension dynamic model. A reentry optimization control problem is developed and the Radau pseudo-spectral method is used to calculate the glide trajectory.

The established dynamic model and trajectory optimization method can effectively simulate the motion process of balloons and UAVs. The system mass reduction for launching UAVs will not cause damage to the balloon structure. The anti-tailspin parachute can reduce the UAV attack angles effectively. The UAV can glide to the designated target position by adjusting the attack angle and sideslip angle. The farthest flight distance after launching from 20 km height is 94 km and the gliding time is 40 min, which demonstrates the potential application advantage of high-altitude launching.

The research content and related conclusions of this article achieve a closed-loop analysis of the flight mission chain for the “balloon-borne UAV system,” which provides simulation references for relevant balloon launching experiments.

This paper establishes a complete set of numerical simulation models and can effectively analyze various postlaunching behaviors.

States that at present wind tunnels are the most commonly used methods for obtaining data on aerofoils and investigating boundary layer phenomena in order to improve laminar flows. Looks at an alternative to wind tunnels – an unmanned aerial vehicle developed by the University of Glasgow – the GUAV‐1. Discusses the work undertaken by the GUAV‐1 as well as its intended uses and aspirations.

The purpose of this paper is to investigate the flow around Parastoo UAV's wing, with the aim of improving its aerodynamic performance. A major source of concern is the use of relatively large flaps in the original design. This unmanned aerial vehicle (UAV) operates at low Reynolds numbers of below 500,000 and was designed for short‐range reconnaissance.

A finite volume solver is utilized to investigate the flow over different wing designs to find a replacement for the current one. To check the accuracy of this numerical modeling, the authors first duplicate the conditions of available relevant experiments. The numerical results are in good agreement with the wind tunnel experiments. Here, the aerodynamic performances of Parastoo's wing at different flight conditions with and without the proposed modification are studied and compared.

As the original design of Parastoo uses relatively large flaps, it is found that the aerodynamic performance of Parastoo is significantly hampered due to their existence. The use of a new wing cross‐section can improve the aerodynamics efficiency of Parastoo. It is recommended that FX‐63137 airfoil is a more suitable cross section instead of Parastoo's original NACA‐63215 airfoil. It is shown that this change improves the aerodynamic performance of the UAV and with the use of smaller flaps (changing the flaperons to only ailerons), the existing payload weight can be increased by 90 per cent.

The issues discussed for this UAV may be of use for other small unmanned plane designers. The numerical data generated for this study are useful for other design teams, both as in direct uses of the data in their own designs and/or for the validation of their numerical methods before investigating other wing designs.

Lockheed Martin has been a premier builder and developer of manned aircraft and fighter jets since 1909. Since then, aircraft design has drastically evolved in many areas including the evolution of manual linkages to fly-by-wire systems, and mechanical gauges to glass cockpits. Lockheed Martin's knowledge of manned aircraft has produced a variety of Unmanned Aerial Vehicles (UAVs) based on size/wingspan, ranging from a micro-UAV (MicroStar) to a hand-launched UAV (Desert Hawk) and up to larger platforms such as the DarkStar. Their control systems vary anywhere between remotely piloted to fully autonomous systems. Remotely piloted control is equivalent to full human involvement with an operator controlling all the decisions of the aircraft. Similarly, fully autonomous operations describe a situation that has the human having minimal contact with the platform. Flight path control relies on a set of waypoints for the vehicle to fly through. This is the most common mode of UAV navigation, and GPS has made this form of navigation practical.

As a standard procedure of human factors engineering, the design of complex systems (e.g., operator interfaces) starts with analyses of system objectives, missions, functions, and tasks. Perceptual Control Theory (PCT) provides a theoretical framework for guiding this process. PCT is founded on notions from control theory, in which closed-loop, negative-gain, feedback systems can be used to build powerful models of goal-directed behavior and for implementing complex systems (Powers, 1973). One of the strengths of PCT over competing human behavior theories is that it explains how humans can control systems that are subject to a wide variety of external influences. UAV control is through the operators’ interaction with the interfaces in remote control stations. A closed-loop feedback system is crucial for both operators and control systems to understand the states and goals of each other. It is likely that advanced UAV control systems will require operators to interact with automated systems such as IAIs. IAIs are sophisticated and will require knowledge about mission goals, the operators’ goals, and states, as well as the UAV and environmental states. Thus, the methods of analysis used in this research were based on PCT given its engineering origins in control theory and advantages accommodating various external disturbances.

SD is defined as a failure to sense correctly the attitude, motion, and/or position of the aircraft with respect to the surface of the earth (Benson, 2003). The types of SD are generally thought to be “unrecognized” and “recognized” (Previc & Ercoline, 2004). Although a third type has been reported (incapacitating), this type seems irrelevant to UAV operations. Unrecognized SD occurs when the person at the controls is unaware that a change in the motion/attitude of the aircraft has taken place. The cause is often the result of a combination of sub-threshold motion and inattention. This type of SD is known to be the single most serious human factors reason for aircraft accidents today, accounting for roughly 90% of all known SD-related mishaps (Davenport, 2000). Recognized SD occurs when a noticeable conflict is created between the actual motion/attitude of the aircraft and any one of the common physiological sensory mechanisms (e.g., visual, vestibular, auditory, and tactile). Recognized SD is the most common type of SD, accounting for the remaining SD-related accidents.

The successful application of the group of unmanned aerial vehicles (UAVs) in the tasks of monitoring large areas is becoming a promising direction in modern robotics. This paper aims to study the tasks related to the control of the UAV group while performing a common mission.

This paper discusses the main tasks solved in the process of developing an autonomous UAV group. During the survey, five key tasks of group robotics were investigated, namely, UAV group control, path planning, reconfiguration, task assignment and conflict resolution. Effective methods for solving each problem are presented, and an analysis and comparison of these methods are carried out. Several specifics of various types of UAVs are also described.

The analysis of a number of modern and effective methods showed that decentralized methods have clear advantages over centralized ones, since decentralized methods effectively perform the assigned mission regardless of on the amount of resources used. As for the method of planning the group movement of UAVs, it is worth choosing methods that combine the algorithms of global and local planning. This combination eliminates the possibility of collisions not only with static and dynamic obstacles, but also with other agents of the group.

The results of scientific research progress in the tasks of UAV group control have been summed up.