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The recommendations set forth in this document are to aid in the design of Unmanned Aircraft (UA) lighting for the size of aircraft and operation for which the aircraft is intended. ...This SAE Aerospace Recommended Practice (ARP) provides technical recommendations for the lighting applications for Unmanned Aircraft Systems (UAS). The technical content of this ARP discusses the unique trade-offs that are necessary to maintain commonality to the U.S.

This document provides an approach to the development of training topics for pilots of Unmanned Aircraft Systems (UAS) for use by operators, manufacturers, and regulators. The identification of training topics is based initially on Practical Test Standard (PTS) topics for manned aircraft pilots. ...The identification of training topics is based initially on Practical Test Standard (PTS) topics for manned aircraft pilots. The topics identified could be used for the construction of a PTS for UAS commercial pilot operations and a PTS for a UAS pilot instrument rating.

Unmanned Aircraft Systems (UAS) emerge as a viable, operational technology for potential civil and commercial applications in the National Airspace System (NAS).

Saft is working on advanced 28V Li-ion batteries for use in NAVY unmanned aircraft applications. This battery employs seven (7) prismatic state-of-the art Li-ion cells connected in series.

This document establishes recommended practices for the specification of general performance, design, test, development, and quality assurance requirements for the flight control related functions of the Vehicle Management Systems (VMS) of military Unmanned Aircraft (UA), the airborne element of Unmanned Aircraft Systems (UAS), as defined by ASTM F 2395-07. ...The document is written for military unmanned aircraft intended for use primarily in military operational areas. The document also provides a foundation for considerations applicable to safe flight in all classes of airspace.

When the flight control system selects the LANDING option at chosen altitude (based on GPS and pressure altitude), a change in aircraft’s attitude is executed. New attitude ensures safe flare and touchdown of the unmanned aircraft. ...The autonomous control of an aircraft under the flare and touch-down maneuvers is an interesting problem of both theoretical and practical nature. ...In this paper, a concept of the autonomous landing system (ALS) for unmanned air vehicles (UAV) is presented. The flight control system is addressed to the low-cost, civilian, medium-size UAV with relatively low approach speed and typical nose-wheel landing gear.

Unmanned Aircraft Systems (UAS) have been growing over the past few years and will continue to grow at a faster pace in future. ...G-31 technical committee of SAE International responsible for electronic transactions for aerospace has published AIR 7356 [1] entitled Opportunities, Challenges and Requirements for use of Blockchain in Unmanned Aircraft Systems Operating below 400ft above ground level for Commercial Use. This paper is a teaser for AIR 7356 [1] document.

The VUSIL program has developed a concept for the integration of unmanned aircraft systems (UAS) into non-segregated airspace, which is also used by manned civil aviation. ...For the integration of UAS it is necessary for the Unmanned Aircraft (UA) pilot to be aware of the surrounding traffic in order to recognise and resolve possible conflicts. ...Collecting the ability requirements of unmanned aircraft pilots was also part of the program. To this end, the UA pilots filled in a job analysis questionnaire to gather first information about the required abilities.

Although Unmanned Aircraft Systems (UAS) have now for some time been used in segregated airspace where separation from other air traffic can be assured, potential users have interests to deploy UAS in non segregated airspace. ...It will be necessary to show that these risks do not increase as compared to the current aviation system with manned aircraft only. This paper focuses on the provision of guidelines for steps 2 to 4 of a UAS SRM process, covering both types of risks. ...A method that addresses potential conflict scenarios (e.g. level busts, aircraft levelling of at the wrong flight level, flight track deviations due to operational errors) is proposed as basis for analysis of the risk of UAS to other airspace users.

A series hybrid-electric propulsion system has been designed for small rapid-response unmanned aircraft systems (UAS) with the goals of improving endurance, providing flexible and responsive electric propulsion, and enabling heavy fuel usage.

The sound produced by Unmanned Aerial Systems (known as UAS or Drones) is often considered to be one of the main barriers (alongside privacy and safety concerns) preventing the widespread use of these vehicles in environments where they may be in close proximity to the general public.

This paper explains why a spark ignited gasoline engine, intake pressurized with three cascaded stages of turbocharging, was selected to power NASA's contemplated next generation of high altitude atmospheric science aircraft. Beginning with the most urgent science needs (the atmospheric sampling mission) and tracing through the mission requirements which dictate the unique flight regime in which this aircraft has to operate (subsonic flight @ >80 kft) we briefly explore the physical problems and constraints, the available technology options and the cost drivers associated with developing a viable propulsion system for this highly specialized aircraft. ...Beginning with the most urgent science needs (the atmospheric sampling mission) and tracing through the mission requirements which dictate the unique flight regime in which this aircraft has to operate (subsonic flight @ >80 kft) we briefly explore the physical problems and constraints, the available technology options and the cost drivers associated with developing a viable propulsion system for this highly specialized aircraft. ...Beginning with the most urgent science needs (the atmospheric sampling mission) and tracing through the mission requirements which dictate the unique flight regime in which this aircraft has to operate (subsonic flight @ >80 kft) we briefly explore the physical problems and constraints, the available technology options and the cost drivers associated with developing a viable propulsion system for this highly specialized aircraft. The paper presents the two available options (the turbojet and the turbocharged spark ignited engine) which are discussed and compared in the context of the flight regime.

The aim of this work is to present the preliminary configuration design studies for an unmanned, lightweight (less than 15 kg), supersonic research aircraft. The studies comprise the aircraft typical mission, the aerodynamic and structural arrangement, preliminary performance, as well as mass distribution. ...The studies comprise the aircraft typical mission, the aerodynamic and structural arrangement, preliminary performance, as well as mass distribution. The aircraft, an Unmanned Air Vehicle, or “UAV”, is named as Pohox (“arrow” in Maxakali indian language). ...The studies comprise the aircraft typical mission, the aerodynamic and structural arrangement, preliminary performance, as well as mass distribution.

The aim of this work is to present the preliminary performance studies of the unmanned, lightweight (less than 10 kg), supersonic research aircraft. The studies comprise the typical mission for the aircraft's first supersonic version, based on the aerodynamic, thrust, and mass characteristics presented in a previous work. ...The studies comprise the typical mission for the aircraft's first supersonic version, based on the aerodynamic, thrust, and mass characteristics presented in a previous work. The aircraft, named as “Pohox”, is an Unmanned Air Vehicle, or “UAV”, and is intended to be the flying test bed for a multi cycle engine capable to provide thrust in subsonic, transonic and supersonic regimes. ...The present analysis can be considered as the natural step, after aircraft first definitions, towards the aircraft detailed design; and the results obtained provide good indications of the technical feasibility of the aircraft.

Thus, a three-dimensional computational fluid dynamics (CFD) model is developed, validated, and used to analyze the D-Dalus L1 four-rotor unmanned aircraft operating under several configurations. The model solves the Euler equations using the OpenFOAM toolbox in order to provide fast results on a desktop computer. ...Such knowledge is, however, of crucial importance to tune the controller and rotor disposition of a cyclogiro aircraft. Thus, a three-dimensional computational fluid dynamics (CFD) model is developed, validated, and used to analyze the D-Dalus L1 four-rotor unmanned aircraft operating under several configurations.

Recent technological developments and increased utilization of Unmanned Aircraft Systems (UAS) have widened their application from military operations to also civil and commercial operations. ...The objective of this paper is to develop and apply a safety risk analysis methodology for the risk of collision of an Unmanned Aircraft System with the ground. Such method could support regulators with the setting of UAS safety requirements. ...To better understand the differences between manned and unmanned aircraft, UAS performance characteristics are examined. This helps to clarify in which airspace classes the different available UAS may be able to fly.

In this paper an automatic procedure aimed at preliminary designing an oleo-pneumatic landing gear strut for a light unmanned aircraft is presented. The whole work is motivated by the necessity to design the landing gear of the unmanned aircraft X-MALE, currently in development at the Italian Aerospace Research Center (CIRA SCpA), according to the Airworthiness Requirements NATO STANAG 4671 (USAR). ...The whole work is motivated by the necessity to design the landing gear of the unmanned aircraft X-MALE, currently in development at the Italian Aerospace Research Center (CIRA SCpA), according to the Airworthiness Requirements NATO STANAG 4671 (USAR). ...Differently from other Airworthiness Requirements for piloted aircraft, USAR.479, “Level Landing” imposes that, in the absence of specific experimental tests, the determination of spin-up and spring-back maximum loads must be carried-out by means of more rational analysis.

Unmanned aircraft systems (UAS), commonly known as drones, are part of a new and budding industry in the United States.