Browse Topic: Flight management systems

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UAVs Swarm Distributed Control based on Artificial Potential FieldF-0081-2025-03805/20/2025
This paper presents a distributed algorithm to track a desired target while fostering the emergence of a swarm formation and providing obstacle avoidance capability to deal with unknown scenarios. The proposed approach is based on the merge between a Flight Management System for global path planning and the definition of virtual forces through a custom Artificial Potential Field to prevent drones collisions between each other, with external objects and to provide cohesion of the swarm configuration. Each drone independently computes its global route and adjusts its path based on an optimal control action to minimize a potential energy function induced by its neighbors and obstacles. This approach results in a high cost-effective strategy to enhance UAVs autonomy level by managing a large group of drones, guaranteeing a low cost per unit thanks to the low computational effort and low-budget sensor suit while providing all the capabilities to accomplish the desired mission.
Cadeddu, Davide
Adopting Aviation Safety Knowledge into the Discussions of Safe Implementation of Connected and Autonomous Road Vehicles2021-01-00744/6/2021
The development of connected and autonomous vehicles (CAVs) is progressing fast. Yet, safety and standardization-related discussions are limited due to the recent nature of the sector. Despite the effort that is initiated to kick-start the study, awareness among practitioners is still low. Hence, further effort is required to stimulate this discussion. Among the available works on CAV safety, some of them take inspiration from the aviation sector that has strict safety regulations. The underlying reason is the experience that has been gained over the decades. However, the literature still lacks a thorough association between automation in aviation and the CAV from the safety perspective. As such, this paper motivates the adoption of safe-automation knowledge from aviation to facilitate safer CAV systems. The authors briefly elaborate on the widely discussed aviation themes, including autopilot and auto-throttle malfunctions, flight management system, human factors, and suggests how this knowledge can improve the safety of road CAVs use-case. Besides, the differences between the safety consideration in the two fields are also denoted. In summary, the main aim of this paper is to highlight the potential benefits of adopting aviation automation safety knowledge into safe CAV development. With the advances in the CAV, the authors are convinced that this subject could serve software developers and engineers in developing safe and standardized CAV technology.
Abdul Hamid, Umar Zakir, Mehndiratta, Mohit, Adali, Erkan
Automatic Pilots (Turbine Powered Subsonic Aircraft)AS440B (Current)12/22/2020
This SAE Aerospace Standard (AS) covers automatic pilots intended for use on aircraft to automatically operate the primary and trim aerodynamic controls to maintain stable flight and/or to provide maneuvering about any of the three axes through servo control. Automatic control functions essential for primary or augmented flight control are excluded.
A-4 Aircraft Instruments Committee
Human Engineering Recommendations for Data Link SystemsARP4791B (Current)11/3/2020
This document sets forth general, functional, procedural, and design criteria and recommendations concerning human engineering of data link systems. The recommendations are based on limited evidence from empirical and analytic studies of simulated data link communication, and on experience from operational tests and actual use of data link. However, because data are not yet available to support recommendations on all potentially critical human engineering issues these recommendations necessarily go beyond the data link research and include requirements based on related research and human factors engineering practice. It is also recognized that evolution of these recommendations will be appropriate as experience with data link accumulates and new applications are implemented. This document focuses primarily on recommendations for data link communications between an air traffic specialist and a pilot, i.e., air traffic services communications, although some recommendations address use of data link for flight information services. Unless otherwise specified within the text, all recommendations apply to both flight deck and ground-based data link systems. This document is intended as a guide for development and evaluation of data link systems. Human engineering considerations are an important element of data link system performance. As illustrated in Figure 1, human engineering recommendations address many component functions required for effective data link communication services in the operational environment. For presentation purposes, the recommendations are divided into five sections: General, functional, procedures, flight deck/air traffic service (ATS) workstation integration, and human-computer interface. To facilitate understanding and use of this document appropriate cross-references to interrelated recommendations appear in parentheses throughout the text.
G-10 Executive Advisory Group
Visual Augmentation for Personal Air Vehicles During Flight Control System DegradationF-0076-2020-1628310/5/2020
Successful human intervention will be central to any emerging autonomous aerial transport platform, such as personal aerial vehicles (PAV), for the safe conduct of flight. This paper proposes a concept to compensate a partial failure of the autonomous flight guidance by handing over control of the aircraft to a passenger and analyzes the associated human factors. First, a novel waypoint guidance law is designed that generates the desired roll commands for navigation to a designated safe landing spot. Second, two novel guidance display concepts are developed, one for the primary flight display (PFD), and another for the helmet mounted display (HMD), which indicate the desired roll commanded by the guidance law. Third, the guidance law and display concepts are integrated into a high-fidelity, wide field-of-view flight simulation environment and a static mock-up of a conventional helicopter cockpit. Humanin-the-loop experiments were performed with test subjects to analyze the effectiveness of the guidance law and display concepts, and to evaluate piloting performance by non-professional pilots. Various mission task elements were analyzed in these experiments and, in order to intensify workload, a disturbance was included together with a guidance law for commanded roll of PAV. Navigation performance, test subjects' ratings and workload are measured by a combination of objective and subjective analyses. Results indicate that all test subjects were able to reach a close vicinity of the landing spot. Furthermore, the HMD concept shows a lower workload with equal or better navigation performance when compared to the PFD concept.
Mehling, Tim, Vrdoljak, Milan, Halbe, Omkar, Heller, Matthias, Hajek, Manfred
A Systems Engineering Approach for Enabling Research and Development in the Vertical Lift Autonomy Flight Sciences DomainF-0076-2020-1636110/5/2020
The objective of the joint National Research Council of Canada (NRC) and The Boeing Company Technology Development Program (TDP) entitled 'Canadian Vertical Lift Autonomy Demonstration' (CVLAD) is to evaluate automated and supervised autonomous flight systems on NRC Bell 412 Advanced Systems Research Aircraft (ASRA) and Royal Canadian Air Force Boeing CH-147F Chinook demonstrators. Boeing technologies such as Degraded Visual Environment Pilotage System and Advanced Vehicle Management System form the foundation of an autonomy solution that aims to satisfy Royal Canadian Air Force, US Army, and other Armed Service branch end-use objectives for force multiplication, tactical advantage, pilot assistance, reduced crew operations, and enhanced fleet productivity. The Boeing Company engaged NRC under a Cooperative Research Agreement since 2016 as part of a number of strategies to upgrade Medium-Heavy Lift H-47 Chinook capabilities prior to long-term aircraft replacement in the 2030 to 2060 timeframe. A recent achievement of the CVLAD TDP by its Boeing Phantom Works, Boeing Chinook Program, Aurora Flight Sciences, and NRC Flight Research Laboratory team was the development of Automated Flight Guidance methods addressing system safety and performance. Design and evaluation activities occurred in Boeing Software-/Hardware in-loop facilities as well as on the NRC Bell 412 ASRA. The CVLAD team is using a blend of traditional Systems Engineering 'V-Shaped' Life Cycle Model, System of Systems, and Model-Based processes to develop a cyber-physical system that aims to meet end-user concept of operations and requirements. Significant benefits of virtual development tools such as component-vehicle digital twins and surrogate inflight simulation facilities are achieved as they promote effective collaboration, efficient design, and relevant verification/validation methodologies. Business models can be made more robust by phasing the introduction of technology where effective automation provides users with near-term benefits, while providing a foundation for safe, reliable, and trusted autonomous capabilities for long-term production.
Alexander, Marc, Spano, Mark, Gowanlock, Derek, Gubbels, Arthur, Dones, Fernando, Rossi, Glenn
DATALINK GROUND SYSTEMS STANDARD AND INTERFACE SPECIFICATION (DGSS/IS)ARINC620-10 (Current)7/31/2020
ARINC Specification 620 defines the interfaces between the Datalink Service Provider (DSP) and the aircraft, other ground-based datalink services, and users. The datalink ground system standard definition supports traditional ACARS and AOA protocols, as well as Media Independent Aircraft Messaging (MIAM) as defined by ARINC Specification 841. MIAM messages can be much larger than ACARS messages (5 MB versus 3.3 kB per message). Supplement 10 improves Controller-Pilot Data Link Communications (CPDLC) by defining a “Deliver By (DB)” period that allows the DSP, that originated the message, to intercept and discard the message if it is not delivered by the specified time. Supplement 10 also adds a Media Advisory code for ACARS over IP (AoIP) indicating that an ACARS non Safety Services messages is being transferred over IP links. New Reason Codes are assigned for un-transmittable or undeliverable messages. ACARS Character set clarifications are also provided in Supplement 10.
Airlines Electronic Engineering Committee
Approach to Landing Guidance System for Transport AircraftARP4102/12B (Current)6/11/2020
This document specifies requirements for an Approach to Landing Guidance System (ALGS) electronic device. This equipment shall display relative aircraft position and situation information for flight along precision three-dimensional paths within the appropriate coverage area. The precision three-dimensional path may be an ILS straight-in look-alike path or a complex, curved path. The requirements are applicable to electronic devices capable of receiving signals or other information from one or more sources, including but not limited to ILS, GNSS, or IRU inputs.
S-7 Flight Deck Handling Qualities Stds for Trans Aircraft
Aerospace - Passive Side Stick Unit General Requirements for Fly-by Wire Transport and BusinessARP6001B (Current)4/23/2020
This SAE Aerospace Recommended Practice (ARP) provides recommendations for design and test requirements for a generic “passive” side stick that could be used for fly-by wire transport and business aircraft. It addresses the following: The functions to be implemented The geometric and mechanical characteristics The mechanical and electrical interfaces The safety and certification requirements
A-6A3 Flight Control and Vehicle Management Systems Cmt
Flight Deck Lighting for Commercial Transport AircraftARP4103A (Current)9/17/2019
This document recommends design and performance criteria for aircraft lighting systems used to illuminate flight deck controls, luminous visual displays used for transfer of information, and flight deck background and instrument surfaces that form the flight deck visual environment. This document is for commercial transport aircraft except for applications requiring night vision compatibility.
A-20A Crew Station Lighting Committee
Flight Testing of Coupled Flight Controls toward Reducing Pilot Workload during Landing in DVEF-0075-2019-145905/13/2019
Landing helicopters in Degraded Visual Environments (DVE) is one of the most challenging maneuvers pilots perform. The U.S. Army Combat Capabilities Development Command, Aviation & Missile Center, Aviation Development Directorate has been working to develop flight guidance and sensor systems to provide the pilot with guidance and pilot cueing to land a helicopter, hover, and take off in DVE. During flight testing of the Brown Out Symbology System (BOSS) on an EH-60L Black Hawk, pilots reported very high workload requiring full concentration on the displays during approaches to landing in brownout. In order to reduce pilot workload, an approach to provide the pilot with a collective tactile cue based on coupling of the output of the approach to landing algorithms to the EH-60L collective trim servo was developed and flight tested. Flight testing of the coupled collective system demonstrated a reduction in pilot workload and increase in the pilot's situational awareness during landing in brownout. To further reduce pilot workload, the pilot cyclic and pedals have been coupled with the guidance symbology to allow for fully coupled landings. Details of the system are provided along with the initial results of flight testing of the system at Felker Army Airfield, Ft. Eustis VA.
LUSARDI, JEFFERY, Fujizawa, Brian, Cleary, Mark
Design and Experimental Evaluation of a Multi-Ship Sensor-Based 3D World Modeling ArchitectureF-0075-2019-147455/13/2019
There is emerging demand for multi-ship sensor-based 3D world modeling (3DWM) for autonomy/cognitive decision aiding avionics applications. In these systems, multiple ships collect and transmit perception sensor data that is fused into a common 3DWM, which is then used by other platforms for flight guidance in that environment. This paper illustrates key design considerations for these systems by exploring the fundamental scenario of leader-follower. This paper will detail the design trade space for the leader-follower scenario, focusing on 3DWM database representation/processing and data transmission. To demonstrate the feasibility of a baseline design approach on modern computing hardware, results will be presented from an experimental evaluation of a proof-of-concept system.
Boggs, Chris, Taylor, Max, Gavrilets, Vladislav
A Dynamic Fault Tree Approach for Time-Dependent Logical Modeling of Autonomous Flight Systems2019-01-13583/19/2019
This paper addresses the urgent need for adequate methodologies to use in analyzing autonomous flight systems, including Unmanned Aircraft. These systems are inherently dynamic and require analysis that is explicitly time dependent. Autonomous flight systems are becoming more commonly used, especially for Part 23 aircraft including Business (Corporate) and Regional Jets or Unmanned Aircraft deployed in hazardous environment/situation. Such systems are expected to make their own decisions under uncertain conditions caused by potential system structure changes when entering a new flight phase or switching to a new system configuration due to system degradation or failure(s) [1]. This paper highlights significant modeling errors that can arise in analyzing dynamic scenarios where these time dependencies are ignored. Model-based solutions are provided by incorporating a time-dependent algebraic formalism into Fault Tree Analysis (FTA) and Dependency Diagram (DD) with updated descriptions in SAE ARP4761A and ARP4754B (Note: These are currently under development). A Dynamic Goal Tree (or alternatively, a Dynamic Dependency Diagram) provides an effective implementation of the time-dependent logic for dynamic system analysis analyzing autonomous flight systems which are inherently dynamic since decisions need to be made without human input in a very short time. The safety analysis for autonomous flight systems, including Unmanned Aircraft, can be performed by extending the traditional phased mission analysis, thus the potential system structure changes for different phases in a flight mission can be expressed by a Dynamic Fault Tree (DFT), or alternatively, a Dynamic Goal Tree (DGT), or Dynamic Dependency Diagram (DDD) [2].
Wang, John
EMBEDDED INTERCHANGE FORMAT FOR OBSTACLE DATABASESARINC815 (Current)12/21/2018
This document defines an open encoding format for obstacle databases. This format, when designed and implemented, will enable a quick, economic, and efficient use of Obstacle Databases (ObsDBs). However, since industry does not require applications to be standardized, data interpretation is not addressed in this document.
Airlines Electronic Engineering Committee
Model-Based Systems Engineering Methodology for Implementing Networked Aircraft Control System on Integrated Modular Avionics – Environmental Control System Case Study2018-01-194310/30/2018
Integrated modular avionics (IMA) architectures host multiple federated avionics applications on a single platform and provide benefits in terms of size, weight, and power, which, however, leads to increased complexity, especially during the development process. To cope efficiently with the high level of complexity, a novel, structured development methodology is required. This paper presents a model-based systems engineering (MBSE) development approach for the so-called “distributed integrated modular architecture” (DIMA). The proposed methodology adapts the open-source Capella tool, based on the Architecture Analysis & Design Integrated Approach (ARCADIA) methodology, to implement a complete design cycle, starting with requirements captured from the aircraft level to streamline the development, culminating in the integration of an avionics application into an ARINC 653 platform. This paper shows how to address the variability of technology implementations at the aircraft and system levels and how the specification artifacts are efficiently managed and traced from the aircraft to the system to the item level to implement the SAE ARP4754A guidelines. The effectiveness of the methodology is presented via a case study of the integration of an environmental control system (ECS) into aircraft control architecture, illustrated for the cabin pressure control system (CPCS). The guidelines derived are applicable to other aircraft systems. In addition, the presented paper provides important insights into the challenges and advantages of the MBSE process over the traditional paper-based specification process.
George Mathew, Prince, Liscouet-Hanke, Susan, Le Masson, Yann
Integrated Rudder and Brake Pedal Unit, General Requirements for Fly-By Wire Transport and Business AircraftARP6252 (Current)10/15/2018
This Aerospace Recommended Practice (ARP) provides general requirements for a generic, integrated rudder and brake pedal unit, incorporating a passive force-feel system that could be used for fixed-wing fly-by wire transport and business aircraft. This ARP addresses the following: The functions to be implemented The mechanical interconnection between captain and F/O station The geometric and mechanical characteristics The mechanical, electrical, and electronic interfaces The safety and certification requirements
A-6A3 Flight Control and Vehicle Management Systems Cmt
ADVANCED FLIGHT MANAGEMENT COMPUTER SYSTEMARINC702A-5 (Current)8/28/2018
The Advanced FMCS provides expanded functions beyond that defined in ARINC 702 to support the anticipated requirements for operation in the CNS/ATM operating environment. GNSS and RNP based navigation, air-to-ground data link for communications and surveillance, and the associated crew interface control/display definitions are included. The NextGen/SESAR concepts and their relative effects on the FMS are addressed in this document. The functional requirements also apply to a Flight Management Function (FMF) in an Integrated Modular Avionics (IMA) architecture with software partitions.
Airlines Electronic Engineering Committee
Vehicle Management Systems - Flight Control Function, Design, Installation and Test of Piloted Military Aircraft, General Specification ForAS94900A (Current)8/13/2018
This SAE Aerospace Standard (AS) provides the general performance, design, installation, test, development, and quality assurance requirements for the flight control related functions of the Vehicle Management Systems (VMS) of military piloted aircraft. It also provides specification guidance for the flight control interfaces with other systems and subsystems of the aircraft.
A-6A3 Flight Control and Vehicle Management Systems Cmt
Guidance on Mitigation Strategies Against Laser Illumination EffectsARP6378 (Current)6/2/2018
This document is intended to give guidance to users, regulators and persons in the aviation field who may be affected by the potential visual interference effects of lasers aimed at aircraft by the general public. The potential effects include startle (distraction, disruption, disorientation, and operational incapacitation), glare, and flashblindness. This document provides mitigation strategies against such effects, including operational procedures, pilot education, and the use of Laser Glare Protection. Prevention of harm from laser eye injuries is discussed but is not a focus of this document, due to the extremely low likelihood of injurious levels of laser light in typical aircraft illumination scenarios. Devices for detecting and reporting hazardous laser illuminations are briefly described in Appendix D, but are not a focus of this document. Some information in this document may also be useful for non-aviation users, such as persons driving vehicles. Additional information can be found in ANSI Z136.6, “Safe Use of Lasers Outdoors”.
G10-OL Operational Laser Committee
ATP360 An Air Carrier First Officer Training ProgramAIR6319 (Current)5/24/2018
ATP360 air carrier training applies to pilots holding a commercial certificate with instrument and multi-engine ratings. This document describes how the ATP360 program achieves its objectives: to educate and train qualified pilots for First Officer and eventually Captain positions with the regional and/or the major airlines. This document also provides an overview of a selection process, an academic curriculum, a flight training program, faculty preparation, and program evaluation. The focus of ATP360 is to develop industry-recognized competencies and instill the knowledge, skills and attitudes required to bring persons up to professional air carrier standards.
G-10G Realistic Training Committee
MULTI-MODE RECEIVER (MMR) - DIGITALARINC755-5 (Current)1/25/2018
ARINC Characteristic 755 defines a multi-mode receiver capable of providing flight path deviation guidance (corrections) to the aircraft during the approach and landing phase. The data source may be from an Instrument Landing System (ILS), a Microwave Landing System (MLS) or an GNSS Landing System (GLS). Supplement 5 adds annunciations defined in RTCA/DO-253D – MOPS for GPS LAAS Airborne Equipment. GNSS Data and GLS Config Validity ARINC 429 Labels are also updated. The range for Selected Glide Path Angle is corrected.
Airlines Electronic Engineering Committee
General Requirements for WDM Backbone NetworksAIR6005 (Current)1/23/2018
This document (AIR6005) provides the framework for the specifications of a WDM OBN within the SAE AS5659 WDM LAN Specification document family, in particular, the Transparent Optical Backbone Network Specification. This framework includes potential requirements, technical background, investigation and context to support the writing of SAE’s WDM LAN specifications documents. The SAE’s AS6005 WDM OBN document describes a transparent optical network which contains optical components and optical interfaces to perform optical transport, optical add/drop, optical amplification, optical routing, and optical switching functions. The conforming optical signal interfaces for the data plane of the WDM OBN are defined. The conforming signal interfaces for the control and management planes of this network are also defined. The control and management plane signals may be either electrical or optical. If successful, a WDM LAN standard is anticipated to include multiple variants that may get created either as separate documents (e.g. a multimode and single-mode specification) and additional documents may be needed to specify the components from which a WDM LAN and OBN will be built. The WDM OBN specification is to be established in a future document, SAE AS5659. This AIR document is a requirements document that provides input regarding the WDM OBN to the AS5659 Aerospace Standard. Additional documents are anticipated to specify aggregation of access for multiple systems that interface to the OBN. The transition from electrical communications links to optically multiplexed networks, is anticipated to involve aggregation of slower speed signals as necessary part of a cost effective transition.
AS-3 Fiber Optics and Applied Photonics Committee
Guide to Civil Aircraft Electromagnetic Compatibility (EMC)ARP60493 (Current)10/25/2017
This guide provides detailed information, guidance, and methods for demonstrating electromagnetic compatibility (EMC) on civil aircraft. This guide addresses aircraft EMC compliance for safety and functional performance of installed electrical and electronic systems. The EMC guidance considers conducted and radiated electromagnetic emissions and transients generated by the installed electrical and electronic systems which may affect other installed electrical and electronic systems on the aircraft. Application of appropriate electrical and electronic equipment EMC requirements are discussed. Methods for aircraft EMC tests and analysis are described. This guide does not address aircraft compatibility with the internal electromagnetic environments of portable electronic devices (PED) or with the external electromagnetic environments, such as high-intensity radiated fields (HIRF), lightning, and precipitation static.
AE-4 Electromagnetic Compatibility (EMC) Committee
Flight Testing of Coupled Collective toward Reducing Pilot Workload during Landing in DVEF-0073-2017-120685/9/2017
ABSTRACT Landing helicopters in Degraded Visual Environments (DVE) is one of the most challenging maneuvers pilots perform. The US Army Aviation and Missile Research, Development and Engineering Center (AMRDEC) has been working to develop flight guidance and sensor systems to provide the pilot with guidance and pilot displays to land a helicopter, hover, and take off in DVE. During flight testing of the Brown Out Symbology System (BOSS) on an EH-60L, pilots reported very high workload requiring full concentration on the displays during approaches to landing in brownout. In order to reduce pilot workload, an approach to provide the pilot with a collective tactile cue based on coupling of the output of the symbology display algorithms to the EH-60L collective trim servo has been developed and flight tested. Details of the system are provided along with the results of flight testing conducted at the Yuma Proving Grounds comparing workload from approaches to landing in brownout with and without the collective coupling engaged.
Lusardi, Jeff, Fujizawa, Brian, Morford, Zachariah
Autopilot, Flight Director, and Autothrust SystemsARP5366 (Current)1/4/2017
This document recommends criteria for the design and installation of Autopilot, Flight Director and Autothrust Systems. These three systems are highly interrelated and will be referred to generically as an Integrated Flight Guidance System (IFGS).
S-7 Flight Deck Handling Qualities Stds for Trans Aircraft
Aeronautical Data Link and Radar Simulator (ADRS)TBMG-2570311/1/2016
Air traffic management research needs to adequately address all players, including flight crews, air traffic controllers/managers, and airline dispatchers. Interactions between the different stakeholders are crucial elements for the viability of a given concept. A simulation capable of addressing this type of distributed decision-making needs to meet several requirements in terms of fidelity, operator proficiency, and number of participants. Most research facilities and laboratories can provide a sufficient fidelity for one particular aspect, but lack in the other aspects because of budget, personnel, and proprietary constraints.
Aircraft Flight Control Systems DescriptionsAIR4094A (Current)7/18/2016
This SAE Aerospace Information Report (AIR) supplies information on the flight control systems incorporated on various current and historic fixed wing, rotary wing, and tilt rotor aircraft. A brief description of the aircraft is followed by a description of the flight control system, some specific components, drawings of the internal arrangement, block diagrams, and schematics. System operation redundancy management is also presented.
A-6A3 Flight Control and Vehicle Management Systems Cmt
Descriptions of Systems Integration Test Rigs (Iron Birds) For Aerospace ApplicationsAIR5992 (Current)10/16/2015
This Aerospace Information Report (AIR) provides information on systems integration rigs, commonly referred to as “Iron Birds” for aerospace applications. a It includes background historical information including descriptions of Iron Birds produced to date, important component elements and selection rationale, hydraulic system design and operational modes and illustrates the design approaches to be considered. b It provides illustrations of the various systems that should be considered for Iron Bird testing in the development phase and utilization during the production program. c It includes recommendations for simulation, component development tests, system integration and lessons learned.
A-6A3 Flight Control and Vehicle Management Systems Cmt
A Novel Approach to Cooperative and Non-Cooperative RPAS Detect-and-Avoid2015-01-24709/15/2015
A unified approach to cooperative and non-cooperative Detect-and-Avoid (DAA) is a key enabler for Remotely Piloted Aircraft System (RPAS) to safely and routinely access all classes of airspace. In this paper state-of-the-art cooperative and non-cooperative DAA sensor/system technologies for manned aircraft and RPAS are reviewed and the associated multi-sensor data fusion techniques are discussed. A DAA system architecture is presented based on Boolean Decision Logics (BDL) for selecting non-cooperative and cooperative sensors/systems including both passive and active Forward Looking Sensors (FLS), Traffic Collision Avoidance System (TCAS) and Automatic Dependent Surveillance - Broadcast (ADS-B). After elaborating the DAA system processes, the key mathematical models associated with both non-cooperative and cooperative DAA functions are presented. The Interacting Multiple Model (IMM) algorithm is adopted to estimate the state vector of the intruders and this is propagated to predict the future trajectories using a probabilistic model. The analytical models adopted to compute the overall uncertainty volume in the airspace surrounding an intruder are outlined. Based on these mathematical models, the SAA Unified Method (SUM) for cooperative and non-cooperative DAA is presented. In this unified approach, navigation and tracking errors affecting the measurements are considered and translated to unified range and bearing uncertainty descriptors, which apply both to cooperative and non-cooperative scenarios. Simulation case studies are carried out to evaluate the performance of the proposed DAA approach on representative host platforms (AEROSONDE RPAS and typical commercial airliners) and various intruder platforms. Results corroborate the validity of the proposed approach and demonstrate the impact of SUM towards providing a cohesive logical framework for the development of an airworthy DAA capability and a pathway for manned/unmanned aircraft coexistence in all classes of airspace.
Ramasamy, Subramanian, Sabatini, Roberto, Gardi, Alessandro
Investigation of GNSS Integrity Augmentation Synergies with Unmanned Aircraft Sense-and-Avoid Systems2015-01-24569/15/2015
Global Navigation Satellite Systems (GNSS) can support the development of low-cost and high performance navigation and guidance architectures for Unmanned Aircraft Systems (UAS) and, in conjunction with suitable data link technologies, the provision of Automated Dependent Surveillance (ADS) functionalities for cooperative Sense-and-Avoid (SAA). In non-cooperative SAA, the adoption of GNSS can also provide the key positioning and, in some cases, attitude data (using multiple antennas) required for automated collision avoidance. A key limitation of GNSS for both cooperative (ADS) and non-cooperative applications is represented by the achievable levels of integrity. Therefore, an Avionics Based Integrity Augmentation (ABIA) solution is proposed to support the development of an Integrity-Augmented SAA (IAS) architecture suitable for both cooperative and non-cooperative scenarios. The performances of this IAS architecture were investigated in representative simulation case studies by testing the ability of the SAA system to exploit the predictive (caution) and reactive (warning) integrity flags generated by ABIA. Additionally, the ABIA False Alarm Rate (FAR) and Detection Probability (DP) performances were examined and an initial evaluation of the complementarity with Space-Based and Ground-Based Augmentation Systems (SBAS/GBAS) was accomplished. Simulation results show that the proposed IAS architecture is capable of performing high-integrity conflict detection and resolution when GNSS is used as the primary source of navigation data and there is a clear synergy with state-of-the art SBAS/GBAS in all applicable flight phases.
Sabatini, Roberto, Moore, Terry, Hill, Chris, Ramasamy, Subramanian
FMS and AFCS Interface for 4D Trajectory Operations2015-01-24589/15/2015
The future revolution of the air traffic system imposes the development of a new class of Flight Management Systems (FMS), capable of providing the aircraft with real-time reference flight parameters, necessary to fly the aircraft through a predefined sequence of waypoints, while minimizing fuel consumption, noise and pollution emissions. The main goal is to guarantee safety operations while reducing the aircraft environmental impact, according to the main international research programs. This policy is expected to affect also the Unmanned Aerial Systems (UASs), as soon as they will be allowed to fly beyond the restricted portions of the aerospace where they are currently confined. In the future, in fact, UASs are expected to fly within the whole civilian airspace, under the same requirements deriving from the adoption of the Performance Based Navigation (PBN). For UASs, the most attractive strategy to reach this goal consists in adopting the mature technology developed for the civil aviation both in terms of operative functions and performance. The current literature lacks of examples dedicated to the control algorithms, which should operate the onboard autopilots and guide the aircraft through the reference calculated trajectory. This paper presents the implementation of a new generation FMS, composed by a trajectory optimization tool and a guidance and control algorithm, interfaced with a suite of proprietary Automatic Flight Control Systems (AFCSs). Different guidance and control algorithms for the FMS are presented and tested on a 6DOF nonlinear mathematical model of a civil aircraft (MASLab), developed within the Clean Sky research program.
Sirigu, Giuseppe, Battipede, Manuela, Gili, Piero, Cassaro, Mario
Simulation-Driven Methodology for the Requirements Verification and Safety Assessment of Innovative Flight Control Systems2015-01-24789/15/2015
The paradigm shift to focus on an enhancement of existing aircraft systems raises the question which of the many possible incremental improvements results in an advantageous solution still considering all existing requirements. Hence, new methodologies for aircraft system design are a prerequisite to cope with such huge and complex design spaces. In the case of flight control system optimization, major design variables are the control surface configuration and actuation as well as their functional allocation. Possible architecture topologies have to be verified inter alia with respect to system safety requirements. In this context, flight dynamic characteristics and handling qualities of the fully operational as well as of several degraded system states of each topology have to be evaluated and checked against common specifications. A model-based verification of the requirements is favorable, resulting in a rapid reduction of the design space. Safety objectives for valid configurations are derived and serve as an input for a subsequent safety assessment. This two-step methodology, a simulation-driven verification of handling quality requirements and a corresponding safety assessment, is presented in this paper. The methodology is intended to support the design engineer in the early concept phase of the system architecture development process. The handling quality analysis is based on a generic flight simulation environment. Using parametric library components, various aircraft and system configurations can be modelled and automatically evaluated via an associated tool suite. Furthermore, an in-house developed analysis tool for system safety is used to carry out the safety assessment based on reliability block diagrams of the flight control architectures. To validate the proposed methodology, an existing, conventional hydraulic-powered flight control system of a single-aisle short-range aircraft is evaluated with respect to its design and safety margins.
Kreitz, Tobias, Bornholdt, Riko, Krings, Matthias, Henning, Karsten, Thielecke, Frank
Aircraft Vertical Route Optimization Deterministic Algorithm for a Flight Management System2015-01-25419/15/2015
This paper describes an optimization algorithm that provides an economical Vertical Navigation profile plan by finding the combinations of climb, cruise and descent speeds, as well as the altitudes for an aircraft to minimize flight costs. The computational algorithm profits from a space search reduction algorithm to reduce the initial number of speed and altitude combinations. Additional search space reductions were performed with the implementation of the branch and cut algorithm. A bounding function that correctly estimates the flight cost considering step climbs was developed to reduce the number of calculations. The full flight fuel burn cost was obtained using a performance database- based method. The fuel flight cost was computed using the cost index. This algorithm used a performance database instead of equations of motion to compute fuel burn. This database was developed and validated by our industrial partner using real flight experimental data. To validate the algorithm, its results were compared against three different algorithms: an “exhaustive search algorithm”, “Branch and Cut” and “Search Space Reduction Algorithm”. The solution provided by the algorithm was also compared to the solution provided by the commercial flight management system used for this study. These comparisons proved that the developed algorithm systematically found the optimal solution, and these solutions were often significantly better than those provided by a commercial flight management system.
Murrieta-Mendoza, Alejandro, Botez, Ruxandra
Development of a High-Fidelity Simulation Model for a Research Environment2015-01-25699/15/2015
During aircraft development, mathematical models are elaborated from our knowledge of fundamental physical laws. Those models are used to gain knowledge in order to make the best decisions at all development stages. Depending on the application, different models can be used to describe, in one way or another, the aircraft behavior. The goal of this paper is to develop a high-fidelity aircraft simulation model that is exceptionally capable, flexible and responsive to the needs of the researchers. The proposed model includes nonlinear aerodynamic coefficients, a generic engine model and a complete autopilot with auto-landing. The simulation model has been designed to help researchers develop and validate new algorithms for trajectory optimization, control design, stability analysis and parameter estimation. To make it easy to use, the simulation model also includes algorithms for stability and control analysis. Methodologies based on Nelder-Mead's optimization algorithm with a friendly user interface have been developed, allowing the trimming and linearizing of an aircraft's model for any flight condition and any configuration. Similarly, the simulation model includes a flight control system (FCS) and a complete autopilot (AP), allowing aircraft to follow a specific trajectory. The FCS and the AP have been designed and tuned using a modified Genetic Algorithm and the Particle Swarm Optimization algorithm. A level D flight simulator of the Cessna Citation X was used to validate the proposed methodology. The results show that the simulation model presented in this paper is accurate and could be further used to analyze the business aircraft Cessna Citation X's behavior. The simulation model could also be adapted for its use on other aircrafts.
Ghazi, Georges, Botez, Ruxandra
Automated ATM System Enabling 4DT-Based Operations2015-01-25399/15/2015
As part of the current initiatives aimed at enhancing safety, efficiency and environmental sustainability of aviation, a significant improvement in the efficiency of aircraft operations is currently pursued. Innovative Communication, Navigation, Surveillance and Air Traffic Management (CNS/ATM) technologies and operational concepts are being developed to achieve the ambitious goals for efficiency and environmental sustainability set by national and international aviation organizations. These technological and operational innovations will be ultimately enabled by the introduction of novel CNS/ATM and Avionics (CNS+A) systems, featuring higher levels of automation. A core feature of such systems consists in the real-time multi-objective optimization of flight trajectories, incorporating all the operational, economic and environmental aspects of the aircraft mission. This article describes the conceptual design of an innovative ground-based Air Traffic Management (ATM) system featuring automated 4-Dimensional Trajectory (4DT) functionalities. The 4DT planning capability is based on the multi-objective optimization of 4DT intents. After summarizing the concept of operations, the top-level system architecture and the key 4DT optimization modules, we discuss the segmentation algorithm to obtain flyable and concisely described 4DT. Simulation case studies in representative scenarios show that the adopted algorithms generate solutions consistently within the timeframe of online tactical rerouting tasks, meeting the set design requirements.
Gardi, Alessandro, Sabatini, Roberto, Ramasamy, Subramanian, Marino, Matthew, Kistan, Trevor
Communication, Navigation and Surveillance Performance Criteria for Safety-Critical Avionic Systems2015-01-25449/15/2015
Avionic system developers are currently working on innovative technologies that are required in view of the rapid expansion of global air transport and growing concerns for environmental sustainability of aviation sector. Novel Communication, Navigation and Surveillance (CNS) system designs are being developed in the CNS/Air Traffic Management (CNS/ATM) and Avionics (CNS+A) context for mission-and safety-critical applications. The introduction of dedicated software modules in Next Generation Flight Management Systems (NG-FMS), which are the primary providers of automated navigation and guidance services in manned aircraft and Remotely-Piloted Aircraft Systems (RPAS), has the potential to enable the significant advances brought in by time and trajectory based operations. High-integrity, high-reliability and all-weather services are required in the context of four dimensional Trajectory Based Operations / Intent Based Operations (TBO/IBO). The NG-FMS and the Next Generation Air Traffic Management (NG-ATM) systems are presented and they allow the development of automated negotiation and validation of the aircraft intents in real-time. After describing the key system architectures, the mathematical models for trajectory generation and CNS performance criteria evaluation are presented. In this paper, the navigation performance is evaluated specifically and in a similar manner, communication and surveillance performances can also be evaluated. An evaluation of the proposed concepts and methodologies is accomplished by modeling and simulation activities. The results demonstrate the functional capability of the novel avionic system to generate cost-effective trajectory profiles satisfying both operational and environmental requirements, as well as satisfying the required navigation performance criteria.
Ramasamy, Subramanian, Sabatini, Roberto
Improvements of the PLANET System for Real-Time Satellite Data Transmission During the HAIC-HIWC Darwin Field Campaign2015-01-21476/15/2015
The PLANET System was used for real-time satellite data transmission during the HAIC-HIWC Darwin field campaign (January to March 2014). The basic system was initially providing aircraft tracking, chat, weather text messages (METAR, TAF, etc.), and aeronautical information (NOTAMs) in a standalone application. In the framework of the HAIC project, many improvements were made in order to fulfill requirements of the onboard and ground science teams for the field campaign. The aim of this paper is to present the main improvements of the system that were implemented for the Darwin field campaign. New features of the system are related to the hardware component, the communication protocol, weather and tracking display, geomarkers on the map, and image processing and compression before onboard transfer.
Turner, Sandra, Gaubert, Jean-Marc, Gallois, Remy, Dacla, Thibault, Mullie, Ingrid, Bourdon, Aurelien, Dezitter, Fabien, Grandin, Alice, Protat, Alain, Potts, Rodney, Schwarzenboeck, Alfons, Strapp, J. Walter
Flight Management System SoftwareTBMG-223016/1/2015
Thales Paris La Défense Cedex, France +33 (0)1 57 77 86 26
Air-Ground Communications System Aims to Make Flying SaferTBMG-222986/1/2015
Reliance on old-fashioned radio contact by pilots and vulnerable tracking systems is still high, but satellites are set to change sky safety, thanks to international collaboration. The European Space Agency’s Iris program is looking to satellites to make aviation safer through modern communications. Worldwide digital data links via satellite, offering much higher capacity, will become the standard for cockpit crews, with voice communications kept as backup.
ADVANCED FLIGHT MANAGEMENT COMPUTER SYSTEMARINC702A-4 (Current)12/15/2014
The Advanced FMCS provides expanded functions beyond that defined in ARINC 702 to support the anticipated requirements for operation in the CNS/ATM operating environment. GNSS and RNP based navigation, air-to-ground data link for communications and surveillance, and the associated crew interface control/display definitions are included.
Airlines Electronic Engineering Committee
Wireless Sensing - Future's Password to Digital Avionics System2014-01-21329/16/2014
Performance of Avionics systems is dictated by the timely availability and usage of critical health parameters. Various sensors are extensively used to acquire and communicate the desired parameters. In today's scenario, sensors are hardwired. The number of sensors is growing due to automation which increases the accuracy of intended Aircraft functions. Sensors are distributed all over the Aircraft and they are connected through wired network for signal processing and communication. LRUs (Line Replaceable Unit) which are integrating various sensors also use a wired approach for communication. The use of a wired network approach poses challenges in terms of cable routing, stray capacitances, noise, mechanical structure and added weight to the structure. The weight of cables contributes significantly to the overall weight of the aircraft. As the weight of Aircraft increases, the required fuel quantity also increases. The Key driver for Airline operational cost is fuel. Fuel quantity is a direct function of weight. Use of wireless sensors in aircraft brings in tremendous advantages in terms of design optimization, flexibility in sensor configuration and weight optimization. Even though the avionics industry is trying to adopt wireless sensors, there are some points of concern in deploying wireless sensors and networks across the aircraft. This paper describes the comparative performance of wired and wireless sensors, type of wireless sensors & interfaces, frequency performance, protocols, network topologies and qualification standards. This paper also discusses the constraints and challenges in deploying wireless sensor network across the aircraft.
Vadgaonkar, Prashant, Janardhan, Ullas, Sivaramasastry, Adishesha
Cessna Citation X Airplane Grey-Box Model Identification without Preliminary Data2014-01-21539/16/2014
An airplane model is usually obtained from preliminary wind tunnel experiments and CFD analysis. These models are then tuned from flight test measurements using system identification, and are used for airplane stability assessment and control design. However, sometimes no or little preliminary data and documentation are available and flight test identification is the main mean to obtain the model needed for control system design. If so, the purpose of this paper is to identify the grey-box model of an airplane without initial data using a combination of the least square and output error estimation methods. A grey-box model identification is preferred because it gives aerodynamic parameter estimations of the airplane. Before flight test data are available, this method was applied to the Cessna Citation X business airplane's high fidelity simulations and carried out with human-in-the-loop on a professional level D flight dynamics simulator designed and manufactured by CAE Inc. More than 1,000 flight simulations were made for different airplane configurations in speeds (140 to 240 kt), altitudes (10,000 to 46,300 ft), masses (24,000 to 33,000 lb) and longitudinal center of gravity positions (17 to 34% of the mean aerodynamic chord). Promising results were obtained for the short period dynamic motion, which allowed the Cessna Citation X's longitudinal stability assessment. The identification method that was used and tested on the research simulator will be used for Hydra Technologies S4 Ehéctatl UAV model identification from real flight test data.
Hamel, Clément, Botez, Ruxandra, Ruby, Margaux
Trajectory Specification for High-Capacity Air Traffic ControlTBMG-195835/1/2014
The doubling or tripling of airspace capacity that will be needed over the next several decades will require that tactical separation guidance be automated for appropriately equipped aircraft in high-density airspace. Four-dimensional (4D) trajectory assignment (three-dimensional position as a function of time) will facilitate such automation. A standard trajectory specification format based on XML (Extensible Markup Language) is proposed for that purpose.
Model-Based Design Flow Driven by Integrated Modular Avionic Simulations2013-01-22119/17/2013
The Integrated Modular Avionics (IMA) architecture has been a crucial concern for the aerospace industry in developing more complex systems, while seeking to reduce space, weight and power (SWaP), as well as development, certification and production time. From a software perspective, that objective pushes developers to migrate toward safety critical space and time partitioning environment. However, mainstream commercial real-time operating systems (RTOS) offering such partitioning can be restrictive in early development due to very high licensing costs. That situation is even more striking when considering that low-cost alternatives could instead be used for system modeling and early simulation before acquisition of a target platform. This paper reviews existing low-cost and open-source development environments to propose a novel design flow. The proposed methodology starts with model-based analysis in the AADL modeling language. Then, configuration files and software integration code are generated and executed using the Simulated IMA (SIMA) software from GMV. A case study experiment was created using a Multi-purpose Control and Display Unit (MCDU) communicating with an external Flight Management System (FMS) simulation provided by our industrial partner CMC Electronics. Results show reduction of time for system and partition configurations from hours to seconds, notably by reducing human error. It also proves useful in identifying design flaws in early development as well as facilitating software architectural exploration for integrated modular avionics.
Savard, Julien, Bao, Lin, Bois, Guy, Boland, Jean-François
Impact of DO-178C on Software Tool Qualification: DO-330 Explored2013-01-21109/17/2013
Software tools are used throughout the life cycle of airborne software. This paper elaborates impact of DO-178C and supplement DO-330 “Software Tool Qualification Considerations” on tool qualification processes as defined in DO-178B. As per DO-178B guidance, software tools are categorized as development tools or verification tools. Software tool qualification process is varied based on this classification. The tool qualification process defined in DO-330 is domain independent. This supplement provides additional guidance, which may be used in qualifying software tools for airborne software, ground-based software, complex electronics hardware, or for other domains. This paper includes discussion on activities and data items associated with tool qualification criteria and corresponding Tool Qualification Levels (TQLs) defined in DO-330. Qualification of Commercial Of-The-Shelf (COTS) tools and in-house developed tools is explained. This paper presents a case study of in-house developed Automated Test Equipment (ATE) tool qualifications process followed as per DO-178B guidance. Impact of DO-178C supplement DO-330 on the ATE tool qualification is studied by comparing with process followed for qualification using DO-178B. The reuse of previously qualified tool to demonstrate compliance with TQL requirements through change impact analysis is also explored.
Bhagat, Preeti, Jingar, Bhupesh
Small Airplane Considerations for the Guidelines for Development of Civil Aircraft and Systems2013-01-22339/17/2013
On September 30, 2011, certification authorities released Advisory Circular 20-174[1], Development of Civil Aircraft and Systems, which recognizes the Society of Automotive Engineers (SAE) Aerospace Recommended Practice (ARP) 4754A and the European equivalent ED-79A [2], in order to address “the concern of possible development errors due to the ever increasing complexity of modern aircraft and systems.” ARP4754A/ED-79A describes a process of development assurance which helps reduce the risk of design errors in the development of aircraft systems. This process is necessary for complex systems not easily comprehended by deterministic analyses or tests. This ARP was developed “in the context of Title 14 of the Code of Federal Regulations (14 CFR) part 25,” a category which includes complex systems such as full fly-by-wire flight controls. However, this paper shows that such systems are the exception to most, recent civil airplane designs. Of new airplanes designed in the last 10 years, most implement systems which are simple and easily comprehended. Many of these simpler aircraft are in the part 23 category, which the AC also associates to this ARP. This paper shows that the ARP, as written, does not consider simple systems and may unnecessarily burden the development of such systems through this lack of recognition. This paper reviews the current diversity of system complexity, discusses the regulatory and technical drivers for this diversity, and provides recommendations for incorporating such considerations in the ARP while preserving its original intent.
Voros, Robert E.
Head Up and Eyes Out Enabling Equivalent Visual Operations with the Head Up Display2013-01-23009/17/2013
Following the introduction of Head-Up Displays (HUD) into commercial airplanes over 30 years ago, many aircraft manufacturers are now installing HUDs as baseline or as a selectable option on their latest designs. Most pilots that have used the HUD in difficult flying conditions prefer it to classic flight deck configurations with head-down displays only. This paper describes the features and benefits of the HUD that allow the pilot to remain head-up and eyes-out throughout the flight, especially in the crowded skies around an airport. This is achievable because the HUD provides all the primary flight information needed to fly the airplane. Some of the information is conformal to the outside world and the whole image is focused at optical infinity, eliminating the need for the pilot to refocus between the HUD symbology and real world features viewed through the HUD. Flight path based flying is intuitive, reducing workload and improving safety by allowing the pilot to maintain better situational awareness of the airplane's energy state. Use of HUD symbology enables increased flight and navigational accuracy to be achieved. Additionally, the HUD provides an advanced monitoring capability for the pilot while the airplane is in automated flight, and allows him/her to independently monitor the control loop, even when not in physical control of the airplane. This paper also discusses the capabilities of the Head-Up Guidance System (HGS™) as related to low visibility operations. Where these operations have been conducted traditionally with automatic guidance systems, the HGS provides the opportunity for pilots to manually conduct the approach, landing and rollout in visibilities as low as 600RVR and takeoffs to 300RVR. Several regulatory “Special Authorizations” have been developed to specifically take advantage of the HUD's low visibility capabilities, to allow increased operational flexibility. The Federal Aviation Administration (FAA) Next Generation Air Transportation System will provide opportunities for Equivalent Visual Operations, which may allow VFR operational tempos, and potentially VFR procedures, to be maintained under low visibility conditions. Vision System technologies, already available on some airplanes, allow HUD symbology to be underlaid with a conformal view of terrain features ahead of the airplane. These technologies, supported by NASA research, allow for the integration of sensor-based Enhanced Vision, Synthetic Vision, and Combined Vision imagery for use both in the air and on the ground. An RTCA committee is defining performance standards for such Vision System technologies. These range from the use of Synthetic Vision, to achieve lower operational minima and increased situational awareness, to the use of sensor-based Enhanced Vision for approach, landing and taxi in visibilities as low as 300RVR. Both analysis and simulator/flight demonstrations, some sponsored by the FAA and NASA, continue to substantiate and quantify the safety benefits that can be realized in flying head-up with a HUD. The results of these studies continue to justify claims that the use of the HUD improves a pilot's accuracy and consistency in performing flight operations, particularly in the terminal area, leading to increased flight safety.
Barber, Sarah, Schwab, Dean, Zimmerman, Ken
Guidelines for the Integration of Electronic Engine Control Systems for Transport Category (Part 25) and General Aviation (Part 23) AircraftAIR5924A (Historical)1/16/2013
This SAE Aerospace Information Report (AIR) provides methodologies and approaches that have been used to install and integrate full-authority-digital-engine-control (FADEC) systems on transport category aircraft. Although most of the information provided is based on turbofan engines installed on large commercial transports, many of the issues raised are equally applicable to corporate, general aviation, regional and commuter aircraft, and to military installations, particularly when commercial aircraft are employed by military users. The word “engine” is used to designate the aircraft propulsion system. The engine station designations used in this report are shown in Figure 1. Most of the material concerns an Electronic Engine Control (EEC) with its associated software, and its functional integration with the aircraft. However, the report also addresses the physical environment associated with the EEC and its associated wiring and sensors. Since most of today’s transport category engines use dual-channel full-authority digital engine control (FADEC) systems, this is the configuration which is addressed. A typical FADEC system configuration is shown in Figure 2.
E-36 Electronic Engine Controls Committee
AOC AIR-GROUND DATA AND MESSAGE EXCHANGE FORMATARINC633-2 (Current)11/28/2012
This document defines the exchange of Aeronautical Operational Control (AOC) message formats used for air-to-ground communication and ground-to-ground communication. ARINC Specification 633 simplifies the integration of AOC software from different suppliers, intended for use by different airlines, on different aircraft types. It is expected that AOC applications will be hosted on an Electronic Flight Bags (EFB). Supplement 2 includes an extensive updates to the Flight Plan schema per ICAO Flight Plan 2012. New XML schemas are added to define AOC messages for airport weather, air traffic information services (ATIS), crew list, passenger list, notice to airmen, pilot report, and hazard advisory.
Airlines Electronic Engineering Committee
Developing an ARINC 661 Cockpit Display System Server with the SCADE Solutions for ARINC 661 Compliant Systems2012-01-211310/22/2012
Embraer began development of an ARINC 661-compliant cockpit display system with Esterel Technologies SCADE Solutions for ARINC 661 Applications. Over the past two years, Embraer has been able to build a fully-functional ARINC 661 demonstrator that includes all components necessary for CDS deployment under the ARINC 661 standard. The ARINC 661 demonstrator includes a fully-compliant ARINC 661 server based originally on Esterel Technologies SCADE 661 Server Creator using an automatic server generator. Embraer had successfully integrated a custom ARINC 661-4, widgets library, with Esterel Technologies widget library, designed with SCADE as the base. Embraer has also developed and integrated User Applications running on a IMA hardware system and communicating with the server using UDP over AFDX within a flight simulator system. This paper discuss the process followed by Embraer for development of the ARINC 661 demonstrator.
Lopes Nunes, Carlos, Mirachi, Samoel, Bento Melo, Alexander, Macauley, John
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