Abstract: Future Unmanned Aircraft Systems (UASs) are expected to be nearly autonomous and composed of heterogeneous Unmanned Aerial Vehicles (UAVs). While most of the current research focuses on UAV avionics and control algorithms, ground task automation has come to the attention of researchers during the past few years. Ground task automation not only relieves human operators, but may also expand the UAS operation area, improve system coverage and enable operation in risky environments without posing a threat to humans. We propose a model to evaluate the coverage of a given UAS. We also compare different solutions for various modules of an automated battery replacement system for UAVs. In addition, we propose a ground station capable of swapping a UAV's batteries, followed by a discussion of prototype components and tests of some of the prototype modules. The proposed platform is well-suited for high-coverage requirements and is capable of handling a heterogeneous UAV fleet.

Abstract: This paper presents a reliability-oriented design (ROD) procedure for three-phase power converters in aircraft applications. These require the highest reliability levels for all its components-as high as space applications; hence the need to maximize the reliability of three-phase power converters, which are in increasing demand and use in commercial and military aircrafts as a result of the more-electric aircraft (MEA) initiative. Specifically, the proposed procedure takes reliability up-front in the design process of power converters, carrying out the design in three steps. First, the identification of critical system components; second, the assessment of reliability factors such as risk analysis, failure mode analysis, and fishbone diagrams; and third, the actual design, which is carried out by minimizing system complexity and stress, and by the use of the most reliable components, materials, and structures. To this end, reliability models were developed for all critical components based on the military handbook MIL-HDBK-217F, and field and vendor data. For verification purposes, the paper includes the ROD of a 60 kW three-phase power converter for aircraft applications together with experimental results of the prototype constructed.

Abstract: AFDX (Avionics Full Duplex Switched Ethernet) standardized as ARINC 664 is a major upgrade for avionics systems. The mandatory certification implies a worst-case delay analysis of all the flows transmitted on the AFDX network. Up to now, this analysis is done thanks to a tool based on a Network Calculus approach. The more recent Trajectory approach has been proposed for the computation of worst-case response time in distributed systems. It has been shown that the worst-case delay analysis of an AFDX network can be improved using an optimized Trajectory approach. This paper extends this optimized approach with the integration of static priority QoS policies. This extension makes possible to compute the bounds needed for deterministic avionics flows (high priority) when (lower priority) non avionics flows are added. Moreover, the paper provides an analysis of the pessimism of the obtained bounds.

Abstract: Methods, systems, and apparatuses for the use of a wireless portable avionics device in conjunction with on-board flight systems and/or off-board service providers. The device may be used by aircraft personnel such as pilots and may act as a command/data entry and/or display tool to augment cockpit display systems. The device can receive flight data (e.g., a flight plan) from an off-board provider and automatically transfer it, as well as any previously prepared commands or data, to a flight management system and/or cockpit display systems. Commands and/or data (including pre-existing ones and ones entered in real-time) can be wirelessly transferred to the on-board flight systems which are not in direct physical contact with the device. Thus, the device can be easily manipulated during turbulence or under poor readability conditions. The device can be used to manipulate items shown on cockpit display systems in a timely and accurate manner.

Abstract: “Fly-By-Wireless” paradigm based on wireless connectivity in aircraft has the potential to improve efficiency and flexibility, while reducing weight, fuel consumption and maintenance costs. In this paper, first, the opportunities and challenges for wireless technologies in safety-critical avionics context are discussed. Then, the assessment of such technologies versus avionics requirements is provided in order to select the most appropriate one for a wireless aircraft application. As a result, the design of a Wireless Avionics Network based on Ultra WideBand technology is investigated, considering the issues of determinism, reliability and security.

Abstract: Systems and methods are provided for FAA-certified avionics devices to safely interface with non-certified mobile telecommunications devices before, during, and after flight. Data transmitted to the certified devices do not affect functionality of the certified device unless and until a user acknowledges and/or confirms the data on the certified device. Thus, the integrity of the certified device is maintained.

Abstract: Loss of engine power constitutes a major emergency situation in General Aviation (GA) aircraft, requiring the location of a safe-to-land strip within reach, and thereupon planning and executing an effective gliding path towards it. These critical tasks are currently entrusted with the pilot. In recent years, technological advances in avionics (GPS, GIS and computing capabilities) have reached the GA cockpit - clearing the way for safety enhancements that utilize these resources. In this paper we consider the problem of 3D trajectory planning for an engine-cut GA aircraft towards a specified airstrip, while avoiding natural or man-made obstacles. We emphasize energy efficiency, which allows the aircraft to maximally extend its reach. To that end we employ a dynamic model of the aircraft, which leads to a six-dimensional optimal control problem. We propose a computation approach that is aimed at approximating the globally optimal solution in real-time. Our approach is based on motion primitives, or basic maneuvers, which are parameterized flight segments of specified shapes which are locally optimized for energy efficiency. These basic maneuvers enable a coarse discretization of the search space, and the planning problem is reduced to a graph-search problem of tractable size which may be efficiently solved using an optimal graph search algorithm. Important computational enhancements include the use of pre-compiled basic maneuver dictionaries. The effectiveness of the proposed solution is demonstrated via simulation results.

Abstract: This review paper summarizes state-of-the-art energy management methods applied to electrical systems of large aircraft. An electrical load management based on fixed priorities of the loads is considered a conventional implementation as applied in today's aircraft systems. It can cut and reconnect loads depending on their importance. The advantages and disadvantages of such a system are presented. Further implementations are depicted that are able to eliminate certain drawbacks of such a typical load management. Most promising is the exploitation of so-called slow responding loads which can be handled like an electrical storage. The optimization potential on future energy management functions is finally discussed and conclusions are drawn.

Abstract: Signaling and inter-system communication in avionics have been crucial topics ever since electronic devices were first used in aerospace systems. To deal with the challenges introduced by the widespread use of general purpose computing in commercial avionics, standards like ARINC 419 and later on 429 were published and adopted by the industry. While in industrial use, 429 has been adapted and extended very little since the standard was formulated in the late 1970s. 429 today cannot meet challenges and new requirements generated by the use of Integrated Modular Avionics and flexible system design. AFDX combines proven safety and availability functionality with modern Ethernet technology to be able to handle today’s requirements. This paper outlines two of the most important avionics network architectures and aims at depicting the evolution of networking concepts and requirements over the course of the past 30 years. It mainly focuses on ARINC 429 and AFDX, the most prominent current and past standards, but also covers two other interesting past protocols.

Abstract: A multi-product avionics control and display unit (CDU). In implementations, the CDU may include a display and a processor coupled with the display. The processor is configurable to operate in a first mode to cause the display to present standby primary flight information associated with the aircraft and a second mode to control and display operation of one or more aircraft systems associated with the aircraft.

Abstract: A flight-operable, truly modular aircraft has an aircraft core to which one or more of outer wings members, fuselage, cockpit, leading and trailing edge couplings, and empennage and tail sections can be removably coupled and/or replaced during the operating life span of the aircraft. In preferred embodiments the aircraft core houses the propulsive engines, avionics, at least 80% of the fuel, and all of the landing gear. The aircraft core is preferably constructed with curved forward and aft composite spars, that transfer loads across the center section, while accommodating a mid-wing configuration. The aircraft core preferably has a large central cavity dimensioned to interchangeably carry an ordnance launcher, a surveillance payload, electronic countermeasures, and other types of cargo. Contemplated aircraft can be quite large, for example having a wing span of at least 80 ft.

Abstract: This paper presents the Quadshot, a novel aerial robotic platform with Vertical Take-Off and Landing (VTOL) capability. Highly dynamic maneuverability is achieved via a combination of differential thrust and aerodynamic surfaces (elevons). The relaxed stability, flying wing, tail-sitter configuration, Radio Controlled (RC) airframe is actively stabilized by onboard controllers in three complementary modes of operation, i.e. hover, horizontal flight and aerobatic flight. In hover mode the vehicle flies laterally, similar to a quadrotor helicopter, can maintain accurate position for aiming payload and land with pinpoint accuracy when equipped with a GPS unit. In horizontal and aerobatic modes it flies like an airplane to cover larger distances more rapidly and efficiently. Dynamic modeling and control algorithms have been discussed before for quadrotors [1]–[4] and classical aircraft configurations, as have other VTOL concepts such as tilt-rotors (eg. the V-22 Osprey) and tail-sitters (eg. the Sydney Univ. T-wing and the Convair XFY-1 Pogo) [5]–[6]. The important contributions of this paper are the combined use of differential thrust in multiple axes and aerodynamic surfaces for flight control, the assisted transition between hover and forward flight control modes with pitch rotation of the entire airframe and the elimination of failure-prone mechanisms for thruster tilting. The development and use of highly extensible Open Source Software and Hardware from the Paparazzi project in a transitioning vehicle is also novel. The vehicle is made highly affordable for both researchers and hobbyists by the use of the Paparazzi Open Source Software [16] and its Lisa embedded avionics suite. Careful attention to the mechanical design promotes large scale manufacturing and easy assembly, further bringing down the cost. The materials selected create a highly durable airframe, which is still inexpensive. Modular airframe design enables quick modification of actuators and electronics, allowing a greater variety of missions. The electronics are also designed to be extensible, supporting the addition of extra sensors and actuators. Custom designed airfoils provide good payload capacity while maintaining 3D aerobatic flight capability; the wing design ensures adequate stability for manual glide control in non-normal situations. This paper covers the software, mechanical and electronic hardware design, control algorithms and aerodynamics associated with this airframe. Experimental flight control results and the design lessons learned are discussed.

Abstract: Advances in airframe and digital avionics during the last century have made the aircraft capable of superior flight and airspace systems incur zero accidents today. Future aircraft and the airspace systems, however, will increasingly rely on “cyber” advances, particularly, in network and information technologies. We envision that “cyber-physical” integration is central to the design and performance of these future aviation information systems. We propose a Cyber-Physical System (CPS) abstraction as a missing framework for future aviation information systems. In this paper, we consider the e-enabled aircraft and Air Traffic Management (ATM) systems as specific CPS instances. We apply our CPS framework to complex interactions between avionics, aircraft internal and external environment, airspace, and off-board systems. Furthermore, we propose a novel avionics-based CPS solution for controlling large volumes of air traffic using the Automatic Dependent Surveillance Broadcast (ADS-B) and airborne networking in ATM. We discuss future challenges with introducing tight cyber-physical integrations in aircraft, including those from evolving dynamics and unpredictability of adverse conditions in cyberspace and physical world.

Abstract: An avionics network demands determinism and predictability. This is especially challenging because of the relatively low bandwidth of the on-board network, and the emerging needs of heterogeneous flows due to the proliferation of avionics applications. Redundant transmission and hard real-time scheduling potentially generate many duplicate data, which makes deduplication become more difficult. Many avionic flows further exhibit dynamic workloads which may change abruptly online. Hence, besides the guarantee of transmission delay, modern avionic network design needs to flexibly handle burst flows and efficiently implement data deduplication for bandwidth saving. In order to address these challenges, we propose a DeDuplication-aware Deficit Round Robin (D2DRR)-based scheduling scheme for Avionics Full DupleX (AFDX) networks with the benefits of low complexity and easy implementation. The core idea is to judiciously offer proper “division of labor” between switches and end systems and transform the services for heterogeneous flows to a single representation of utilization, i.e., DRR quantum, which can be flexibly reconfigured. We further leverage Bloom filters to support fast deduplication in order to reduce the load on the AFDX network. D2DRR, hence, offers salient features, elastic scheduling and adept deduplication, to deliver substantial performance improvements. Through both simulations and real implementations, extensive experimental results in an AFDX testbed demonstrate the efficacy and efficiency of our proposed schemes.

Abstract: The paper presents the EU funded MADES FP7 project, that aims to develop an effective model driven methodology to evolve current practices for the development of real time embedded systems for avionics and surveillance industries. In MADES, we propose an effective SysML/MARTE language subset and have developed new tools and technologies that support high level design specifications, validation, simulation and automatic code generation, while integrating aspects such as component re-use. The paper first illustrates the MADES methodology by means of a car collision avoidance system case study, followed by the underlying MADES language design phases and tool set which enable verification and automatic code generation aspects, hence enabling implementation in execution platforms such as state of the art FPGAs.

Abstract: 1. For carrying remote sensing or other scientific payloads. Highly publicized examples of such applications include the forest fire detection effort jointly conducted by NASA Ames research centre and the US Forest Service (Ambrosia et al., 2004), and the mission into the eye of hurricane Ophelia by an Aerosonde® UAV (Cione et al., 2008); 2. For evaluating different sensing and decision-making strategies as an autonomous vehicle. For examples, an obstacle and terrain avoidance experiment was performed at Brigham Young University to navigate a small UAV in the Goshen canyon (Griffiths et al., 2006); an autonomous formation flight experiment was performed at West Virginia University (WVU) with three turbine-powered UAVs (Gu et al., 2009); 3. As a sub-scale test bed to help solving known or potential issues facing full-scale manned aircraft. For example, a series of flight test experiments were performed at Rockwell Collins (Jourdan et al., 2010) with a sub-scale F-18 aircraft to control and recover the aircraft after wing damages. Another example is the X-48B blended wing body aircraft (Liebeck, 2004) jointly developed by Boeing and NASA to investigate new design concepts for future-generation transport aircraft.

Abstract: The Traffic Alert and Collision Avoidance System significantly reduces the risk of mid-air collision and is mandated worldwide on transport aircraft. Engineering the avoidance logic was costly and ...

Abstract: The Integrated Modular Avionics (IMA) architecture has been suggested for the next-generation avionics systems. ARINC 653 is the standard for application programming interfaces (APIs) of avionics software for IMA architecture. There are several researches on design and implementation of ARINC 653 but legacy operating systems have not been considered much for a base operating system of ARINC 653. Though the legacy operating systems may not be initially developed for avionics systems, some of them including Linux recently show high potential of providing software platform for avionics systems. In this paper, we suggest a kernel-level design to support partitioning and hierarchical real-time scheduling of ARINC 653 for Linux. We believe that our suggestion can provide a very valuable reference for extending an existing operating system for ARINC 653 especially due to the complexity of the Linux kernel. We show that the overhead and jitter of the proposed design is significantly low compared with a user-level design.

Abstract: Safety critical systems (e.g., an avionics control system for safe flight) are often required to achieve certification under pre-established standards (e.g., DO-178B for software considerations in airborne systems and equipment certification). We have been working with our industrial partner for the last three years to develop product line assets for their avionics software product line (SPL) and, recently, we encountered two major challenges regarding certification. Firstly, an individual product must be certified, but each may require a different certification level: there might be variations in the certification requirements according to specific system usage contexts. Secondly, certification involves not only product but also process, as standards such as DO-178B also assess the quality of the development process. In this paper, we propose to include a certification view during feature modelling to provide a better understanding of the relationships between features and a certification level required for each product. The experience of introducing certification into the design model of an Unmanned Aerial Vehicle (UAV) SPL is presented to illustrate some key ideas. We also describe the lessons we have learned from this experience.

Abstract: Failure of electronic devices is a concern for future electric aircrafts that will see an increase of electronics to drive and control safety-critical equipment throughout the aircraft. As a result, investigation of precursors to failure in electronics and prediction of remaining life of electronic components is of key importance. DC-DC power converters are power electronics systems employed typically as sourcing elements for avionics equipment. Current research efforts in prognostics for these power systems focuses on the identification of failure mechanisms and the development of accelerated aging methodologies and systems to accelerate the aging process of test devices, while continuously measuring key electrical and thermal parameters. Preliminary model-based prognostics algorithms have been developed making use of empirical degradation models and physics-inspired degradation model with focus on key components like electrolytic capacitors and power MOSFETs (metal-oxide-semiconductor-field-effect-transistor). This paper presents current results on the development of validation methods for prognostics algorithms of power electrolytic capacitors. Particularly, in the use of accelerated aging systems for algorithm validation. Validation of prognostics algorithms present difficulties in practice due to the lack of run-to-failure experiments in deployed systems. By using accelerated experiments, we circumvent this problem in order to define initial validation activities.

Abstract: The X-MAN tool has been developed in the European project CESAR, for component-based system development. CESAR is a large industrial project that aims to develop a component-based technology that can be used for developing embedded systems in multiple domains, including automotives and avionics. X-MAN has been successfully evaluated by CESAR's external reviewers and internally by Airbus Operations Limited for the avionics domain. X-MAN is designed and implemented using MDE, in this paper we describe its design and implementation.

Abstract: Embodiments of the present invention provide improved systems and methods for a programmable portable electronic device for airborne operational communications. In one embodiment, a method comprises loading application configuration information onto a storage medium on the portable electronic device from an external storage medium, the application configuration information defining an application configuration for the avionic operational data communications application and configuring an avionic operational data communications application stored in the storage medium on the portable electronic device according to the application configuration information stored in the the storage medium. Further, the method includes receiving avionic operational data from an airborne server; executing the avionic operational data communications application to process the avionic operational data, wherein the execution of the avionic operational data communications application produces operational communications according to the application configuration information stored in the storage medium; and communicating the operational communications with a ground peer.

Abstract: Tohoku University is now developing an international scientific micro-satellite named RISESAT (Rapid International Scientific Experiment Satellite), whose launch is planned to be in the end of 2013. RISESAT is a 50-kg class micro-satellite. The orbit is planned to be a sun-synchronous orbit with an altitude of around 700km. RISESAT will carry 6 international scientific payloads developed by overseas partners, including a high-precision telescope with liquid crystal tunable filters with 5m GSD, as well as an optical communication terminal as technology demonstration. The total weight of payload instruments sums up to more than 10kg which is about 20 % of the whole satellite. RISESAT employs a payload main computer based on Space Plug and Play Avionics (SPA) technology for controlling all of these scientific instruments. By applying virtual system integration technology, remote integration of satellite components spread all over the world becomes possible without getting together at a certain place. In this way the integration of a variety of payload instruments becomes simple and the effort required can be dramatically reduced. RISESAT project is now at the end of Engineering Model development phase and has experienced first mechanical and electrical integration activity of the Engineering Models of payload instruments.

Abstract: This paper describes operations and procedures envisioned for NASA's Air Traffic Management (ATM) Technology Demonstration #1 (ATD-1). The ATD-1 Concept of Operations (ConOps) demonstration will integrate three NASA technologies to achieve high throughput, fuel-efficient arrival operations into busy terminal airspace. They are Traffic Management Advisor with Terminal Metering (TMA-TM) for precise time-based schedules to the runway and points within the terminal area, Controller-Managed Spacing (CMS) decision support tools for terminal controllers to better manage aircraft delay using speed control, and Flight deck Interval Management (FIM) avionics and flight crew procedures to conduct airborne spacing operations. The ATD-1 concept provides de-conflicted and efficient operations of multiple arrival streams of aircraft, passing through multiple merge points, from top-of-descent (TOD) to touchdown. It also enables aircraft to conduct Optimized Profile Descents (OPDs) from en route altitude to the runway, using primarily speed control to maintain separation and schedule. The ATD-1 project is currently addressing the challenges of integrating the three technologies, and implantation into an operational environment. Goals of the ATD-1 demonstration include increasing the throughput of high-density airports, reducing controller workload, increasing efficiency of arrival operations and the frequency of trajectory-based operations, and promoting aircraft ADS-B equipage.

Abstract: As the software for avionics becomes more complex, the challenge to provide the required reliability and safety mechanisms becomes also more complex. Embracing the ARINC 650 and 653 standards to provide a means to embark several systems into a single hardware cabinet opens the door to the development of even more elaborated software avionics systems, by overcoming the space constraints once found in this kind of system. Nevertheless, ARINC 653 exhibits also some limitations regarding fault redundancy management, especially when handling redundant applications with spares that back up other applications. In this paper, a framework to support fault tolerance and reconfiguration in avionics systems under the umbrella of ARINC 653 standard is described. This paper represents part of the results of the research projects carried out during the last two years by Eurocopter Espana in collaboration with the University of Castilla-La Mancha.

Abstract: Disclosed is an aircraft avionics ground test system based on a PXI bus and Lab Windows Cvi. The system is composed of a hardware part and a software part, wherein their relationship is that the hardware part and the software part cooperate to achieve the functions of data acquiring, test result displaying, judging and recording. The hardware part is composed of a PXI test system, an adapter, an I/O module, an equipment cabinet, a test bench, a test cable and a power supply. The contents and procedures of the software part are as follows: firstly, a development environment is established and a test system application software engineering is established in the development environment; then, a test system software is designed according to time-driven task, event-driven task and background-run task; and finally, the design is initialized, service procedures are interrupted by a clock, and procedures are handled by an interface, wherein the whole operation process shows design in such aspects as software task division, task priority setting, task scheduling, communication between tasks, and display interface. The aircraft avionics ground test system provided by the invention has the advantages of modularization, integration and miniaturization in design.

Abstract: Wireless communications has more to offer for spacecraft avionics than just reduced mass and space. A team at NASA Ames Research Center (ARC) is actively involved in designing and implementing wireless systems, and is part of a multi-center NASA effort to investigate wireless sensor networks (WSN) for spacecraft sponsored by the NASA Engineering and Safety Center. In this paper, we describe an implementation of ZigBee run over an IEEE 802.16.2 network architecture, and explain how this topology can be adapted to meet the rigorous challenges presented by the space environment. We present current ZigBee applications and deployments and compare ZigBee with some competing network architectures. We also present some of the wireless sensor network research and development that has been accomplished at ARC and discuss future plans. Our results show that ZigBee can meet requirements and provide the opportunity to develop a smart spacecraft infrastructure modeled on the “smart home” vision, and outline some steps that might be taken to bring this model to reality.