Civil aircraft advanced avionics architectures - an insight into saras avionics, present and future perspective

Traditionally, the avionics architectures being implemented are of federated nature, which means that each avionics function has its own independent, dedicated fault-tolerant computing resources. Federated architecture has great advantage of inherent fault containment and at the same time envelops a potential risk of massive use of resources resulting in increase in weight, looming, cost and maintenance as well. With the drastic advancement in the computer and software technologies, the aviation industry is gradually moving towards the use of Integrated Modular Avionics (IMA) for civil transport aircraft, potentially leading to multiple avionics functions housed in each hardware platform. Integrated Modular Avionics is the most important concept of avionics architecture for next generation aircrafts. SARAS avionics suite is purely federated with almost glass cockpit architecture complying to FAR25. The Avionics activities from the inception to execution are governed by the regulations and procedures under the review of Directorate General of Civil Aviation (DGCA). Every phase of avionics activity has got its own technically involvement to make the system perfect. In addition the flight data handling, monitoring and analysis is again a thrust area in the civil aviation industry leading to safety and reliability of the machine and the personnel involved. NAL has been in this area for more than two decades and continues to excel in these technologies

Code Generation for Safety-Critical Systems

International audienceThe number of safety-critical systems in vehicles is rapidly increasing. A few years ago, the failure of a computersystem in a vehicle would in the worst case mean the loss of a function, but in the systems of the future, the wrongreaction to a fault may be a safety hazard for the vehicle’s occupants and other road users

Systems study for an Integrated Digital-Electric Aircraft (IDEA)

The results of the Integrated Digital/Electric Aircraft (IDEA) Study are presented. Airplanes with advanced systems were, defined and evaluated, as a means of identifying potential high payoff research tasks. A baseline airplane was defined for comparison, typical of a 1990's airplane with advanced active controls, propulsion, aerodynamics, and structures technology. Trade studies led to definition of an IDEA airplane, with extensive digital systems and electric secondary power distribution. This airplane showed an improvement of 3% in fuel use and 1.8% in DOC relative to the baseline configuration. An alternate configuration, an advanced technology turboprop, was also evaluated, with greater improvement supported by digital electric systems. Recommended research programs were defined for high risk, high payoff areas appropriate for implementation under NASA leadership

Usage of Fault Detection Isolation & Recovery (FDIR) in Constellation (CxP) Launch Operations

This paper will explore the usage of Fault Detection Isolation & Recovery (FDIR) in the Constellation Exploration Program (CxP), in particular Launch Operations at Kennedy Space Center (KSC). NASA's Exploration Technology Development Program (ETDP) is currently funding a project that is developing a prototype FDIR to demonstrate the feasibility of incorporating FDIR into the CxP Ground Operations Launch Control System (LCS). An architecture that supports multiple FDIR tools has been formulated that will support integration into the CxP Ground Operation's Launch Control System (LCS). In addition, tools have been selected that provide fault detection, fault isolation, and anomaly detection along with integration between Flight and Ground elements

Dependable and Certifiable Real-World Systems – Issue of Software Engineering Education

Embedded software and dedicated hardware are vital elements of the modern world, from personal electronics to transportation, from communication to aerospace, from military to gaming, from medical systems to banking. Combinations of even minor hardware or software defects in a complex system may lead to violation of safety with or even without evident system failure, a major problem that the computing profession faces is the lack of a universal approach to unite the dissimilar viewpoints presented by computer science, with its discrete and mathematical underpinnings, and by computer engineering, which focuses on building real systems and considering spatial and material constraints of space, energy, and time. Modern embedded systems include both viewpoints: microprocessors running software and programmable electronic hardware created with an extensive use of software. The gap between science and engineering approaches is clearly visible in engineering education. This survey paper focuses on exploring the commonalities between building software and building hardware in an attempt to establish a new framework for rejuvenating computing education, specifically software engineering for dependable systems. We present here a perspective on software/hardware relationship, aviation system certification, role of software engineering education, and future directions in computing

High-speed civil transport flight- and propulsion-control technological issues

Technology advances required in the flight and propulsion control system disciplines to develop a high speed civil transport (HSCT) are identified. The mission and requirements of the transport and major flight and propulsion control technology issues are discussed. Each issue is ranked and, for each issue, a plan for technology readiness is given. Certain features are unique and dominate control system design. These features include the high temperature environment, large flexible aircraft, control-configured empennage, minimizing control margins, and high availability and excellent maintainability. The failure to resolve most high-priority issues can prevent the transport from achieving its goals. The flow-time for hardware may require stimulus, since market forces may be insufficient to ensure timely production. Flight and propulsion control technology will contribute to takeoff gross weight reduction. Similar technology advances are necessary also to ensure flight safety for the transport. The certification basis of the HSCT must be negotiated between airplane manufacturers and government regulators. Efficient, quality design of the transport will require an integrated set of design tools that support the entire engineering design team

Use of Model-Based Software Product Line Engineering for Certifiable Avionics Software Development

RÉSUMÉ Tous les systèmes logiciels avioniques sont soumis aux contraintes de certification imposées par les normes DO-178. Les fabricants d’équipements avioniques civils sont très conservateurs dans leur processus de développement de logiciels et la plupart utilisent encore des outils et des méthodes d’ingénierie logicielle éprouvés en raison des contraintes de certification strictes. Les contraintes de certification, avec la taille et la complexité du logiciel des systèmes avioniques modernes qui augmentent continuellement, ont un impact considérable sur le coût du développement de logiciel avionique certifiable. Pour réduire le coût de développement, les fabricants d’équipements avioniques doivent utiliser des méthodes de développement logiciel modernes, ce qui est possible avec la publication de la norme DO-178C. Dans le cadre de ma thèse, nous explorons l’utilisation de l’ingénierie de ligne de produit basée sur des modèles pour le développement de logiciels avioniques certifiables et proposons des solutions au niveau industriel pour utiliser un processus de ligne de produit utilisant des outils commerciaux. Dans le cadre de ma thèse, nous explorons également l’applicabilité de notre processus de development logiciel basé sur le concept de ligne de produit au développement de logiciels avioniques certifiables contrôlés. Nous identifions les contraintes qui limitent la réutilisation des composants logiciels dans les logiciels avioniques sous contrôle d’exportation et proposons des solutions techniques qui facilitent l’application de ligne de produit logiciel basée sur des modèles au développement de logiciels avioniques certifiés et sous contrôle d’exportation. Nous validons nos solutions proposées par des études de cas industriels.----------ABSTRACT All avionics software systems are subjected to certification constraints imposed by DO-178 standards. Civil avionics equipment manufacturers are quite conservative in their software development processes: most still use time-tested software engineering tools and methods, due to strict certification constraints. These certification constraints, along with the increasing size and complexity of modern avionics software-intensive systems, are having a huge impact on the cost of certifiable avionics software development. To cope with this increasing complexity, avionics equipment manufacturers need to use modern software development methodologies. This is possible with the release of DO-178C standard. In my thesis, I have explored the use of model-based software product line engineering for certifiable avionics software development, and have proposed industrial-level solutions for using a model-based software product line process based on commercially available tools. In this thesis, I have also explored the applicability of our model-based software product line process to export-controlled, certifiable avionics software development, identifying constraints that limit the reuse of software components among export-controlled avionics software and proposing technical solutions that facilitate the application of a model-based software product line to export-controlled, certifiable avionics software development. The proposed solutions are validated using industrial case studies

High speed research system study. Advanced flight deck configuration effects

In mid-1991 NASA contracted with industry to study the high-speed civil transport (HSCT) flight deck challenges and assess the benefits, prior to initiating their High Speed Research Program (HSRP) Phase 2 efforts, then scheduled for FY-93. The results of this nine-month effort are presented, and a number of the most significant findings for the specified advanced concepts are highlighted: (1) a no nose-droop configuration; (2) a far forward cockpit location; and (3) advanced crew monitoring and control of complex systems. The results indicate that the no nose-droop configuration is critically dependent upon the design and development of a safe, reliable, and certifiable Synthetic Vision System (SVS). The droop-nose configuration would cause significant weight, performance, and cost penalties. The far forward cockpit location, with the conventional side-by-side seating provides little economic advantage; however, a configuration with a tandem seating arrangement provides a substantial increase in either additional payload (i.e., passengers) or potential downsizing of the vehicle with resulting increases in performance efficiencies and associated reductions in emissions. Without a droop nose, forward external visibility is negated and takeoff/landing guidance and control must rely on the use of the SVS. The technologies enabling such capabilities, which de facto provides for Category 3 all-weather operations on every flight independent of weather, represent a dramatic benefits multiplier in a 2005 global ATM network: both in terms of enhanced economic viability and environmental acceptability

Real-Time Hazard Detection and Avoidance Demonstration for a Planetary Lander

The Autonomous Landing Hazard Avoidance Technology (ALHAT) Project is chartered to develop and mature to a Technology Readiness Level (TRL) of six an autonomous system combining guidance, navigation and control with terrain sensing and recognition functions for crewed, cargo, and robotic planetary landing vehicles. In addition to precision landing close to a pre-mission defined landing location, the ALHAT System must be capable of autonomously identifying and avoiding surface hazards in real-time to enable a safe landing under any lighting conditions. This paper provides an overview of the recent results of the ALHAT closed loop hazard detection and avoidance flight demonstrations on the Morpheus Vertical Testbed (VTB) at the Kennedy Space Center, including results and lessons learned. This effort is also described in the context of a technology path in support of future crewed and robotic planetary exploration missions based upon the core sensing functions of the ALHAT system: Terrain Relative Navigation (TRN), Hazard Detection and Avoidance (HDA), and Hazard Relative Navigation (HRN)