Browse Topic: Flight control systems

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Guidelines for the Integration of Electronic Engine Control Systems for Transport Category (Part 25) and General Aviation (Part 23) AircraftAIR5924B (Current)11/26/2025
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
E-36 Electronic Engine Controls Committee
Aerospace - Test Methodology for Electrohydrostatic ActuatorsARP5879A (Current)11/26/2025
This document provides an overview of the tests and issues related to testing that are unique to Electrohydrostatic Actuators (EHAs). An EHA incorporates a linear or rotary hydraulic actuator and a variable speed, reversible electric servomotor driving a fixed displacement hydraulic pump for actuator control, and associated power drive electronics. The tests and issues documented are not necessarily all-inclusive. This document discusses both, the tests applicable to EHAs and the test methodologies to accomplish the test objectives. This document also lists tests that are not unique to EHAs, but are still applicable to EHAs. In these instances a discussion of such tests is not contained in this document, and as applicable, the reader may reference ARP1281 (Actuators: Aircraft Flight Controls, Power Operated, Hydraulic, General Specification For), which addresses test issues applicable to electrohydraulic flight control servoactuators. In the discussion of the tests and test
A-6B2 Electrohydrostatic Actuation Committee
Electrohydrostatic Actuation Applications on Aircraft ProgramsAIR6353 (Current)11/26/2025
This document will maintain a listing of all current and new EHA/EBHA aircraft applications, including parameters such as power, force, rate, etc, as is permissible for public offering.
A-6B2 Electrohydrostatic Actuation Committee
IAQG-03282025-1 IAQG-03282025-1 (Current)04/02/2025
IAQG-03282025-1
IAQG-1 Standards Committee
Designing an Uncrewed Aircraft Systems Control Model for an Air-to-Ground Collaborative System01-17-02-001402/19/2024
Abstract In autonomous technology, uncrewed aircraft systems have already become the preferred platform for the research and development of flight control systems. Although they are subjected to following and satisfying complicated scenarios of control stations, this high dependency on a specific control framework limits them in their application process and reduces the flight self-organizing network. In this article, we present a developed multilayer control system protocol with the additional supportive manned aircraft layer (Tender). The novelty of the introduced model is that uncrewed aircraft systems are monitored and navigated by the tender, and then based on the suggested scheme, data flows are controlled and transferred across the network by the developed cloud–robotics approach in the ground station layer. Therefore, it has been tried to design a semi-autonomous control network to gather data that combines human observation and the automotive nature of uncrewed aircraft
Millar, Richard C., Laliberté, Jeremy, Mahmoodi, Armin, Hashemi, Leila, Meyer, Robert Walter
External Synchronization of Distributed Redundant Flight Control Computers01-17-02-001012/01/2023
This work introduces a practical approach to external synchronization for flight control computers (FCCs) deployed in a decentralized fashion. The internal synchronization among the FCCs in distributed flight control systems needs to be extended for specific applications, necessitating an urgent need for an external synchronization mechanism. For instance, when the air data and attitude reference system (ADAHRS) and the flight control computer (FCC) are not synchronized, a dead time or time offset occurs between the time the ADAHRS transmits data and the time the FCC begins executing its control functions, which can impair flight control system performance or even cause system instability, particularly for the system with incremental control approaches, such as incremental nonlinear dynamic inversion (INDI). Therefore, an external synchronization technique that does not rely on establishing a global view of time that is accurately synchronized with an external reference device has been
Khozin, Mokhamad, Holzapfel, Florian
Detection & Tracking of Multi-Scenic Lane Based on Segnet-LSTM Semantic Split Network2021-01-008304/06/2021
Lane detection is an important component in automatic pilot system and advanced driving assistance system (ADAS). The stability and precision of lane detection will directly determine precision of control and lane plan of vehicles. Traditional mechanical vision lane detection approaches in complicated environment have the deficiencies of low precision and feature semantic description disabilities. But the lane detection depending on deep learning, e.g. SCNN network, LaneNet network, ENet-SAD network have imbalance problems of splitting precision and storage usage. This paper proposes an approach of high-efficiency deep learning Segnet-LSTM semantic segmentation network. This network structure is composed with encoding network and corresponding decoding networks. First, convolution and maximum pooling. The proposal extracts texture details of five images and stores searching position of maximum pooling. Meanwhile, it will implement interpolate processing to the lost points. Then, by up
Ye, Meng, Tan, Gangfeng, Tang, Jingning, Feng, Jiaming, Huang, Xin, Sun, Wenchao
Graphic Symbols for Aircraft Hydraulic and Pneumatic SystemsAS1290C (Current)02/12/2021
This SAE Aerospace Standard (AS) provides a system of graphic symbols and line codings that are intended primarily for usage in hydraulic and pneumatic system schematic diagrams for all types of aircraft.
A-6 Aerospace Actuation, Control and Fluid Power Systems
Graphic Symbols for Aircraft Hydraulic and Pneumatic SystemsAS1290C-TEST-REC (Historical)02/12/2021
This SAE Aerospace Standard (AS) provides a system of graphic symbols and line codings that are intended primarily for usage in hydraulic and pneumatic system schematic diagrams for all types of aircraft.
A-6 Aerospace Actuation, Control and Fluid Power Systems
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
Flight Test Procedures for Static Pressure Systems Installed in Subsonic Transport AircraftARP921B (Current)12/22/2020
This SAE Aerospace Recommended Practice (ARP) covers the test procedures and equipment for performing flight testing on pitot-static systems installed in subsonic transport type aircraft.
A-4 Aircraft Instruments Committee
Aerospace Fluid Power - Contamination Sensitivity - Considerations for Establishing Test Procedures for Flight Control ActuatorsARP5941 (Current)10/09/2020
This SAE Aerospace Recommended Practice (ARP) describes the design conditions under which tests should be conducted to demonstrate satisfactory performance of a flight critical servo-actuator under the maximum allowable particulate contamination in the associated airplane hydraulic system. Additionally, this document also describes the recommended tests and the required acceptance criteria.
A-6B1 Hydraulic Servo Actuation Committee
SAE TOMORROW TODAY: Constant Innovation in Aviation1290108/07/2020
As the innovation center for Airbus, Acubed is bringing the Silicon Valley approach to advancement to the aerospace industry. Mark Cousin, CEO of Acubed, joins host Grayson Brulte for an in-depth conversation on the aviation innovations that Acubed is working on to improve efficiency and safety. Mark shares with us the important developments that Acubed and Airbus have made over the past 10-15 years to help the organization achieve year-over-year efficiencies; how Acubed has evolved over the past five years to become a more targeted innovation center; and some of the specific innovations, including Fly by Wire, Project Wayfinder and ATOL, that demonstrate the importance of machine learning and AI to enable autonomy that will improve safety of commercial aviation, reduce costs and address the pilot shortage. He also gives a sneak peek at some of the current and future projects in the works at Acubed that will advance Airbus' vision for innovation, including unmanned traffic management
Hineman, Marcie
DATALINK GROUND SYSTEMS STANDARD AND INTERFACE SPECIFICATION (DGSS/IS)ARINC620-10 (Current)07/31/2020
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
Aircraft Ground Deicing/Anti-Icing Training and Qualification ProgramAS6286B (Historical)06/11/2020
This document establishes the minimum training and qualification requirements for ground-based aircraft deicing/anti-icing methods and procedures. All guidelines referred to herein are applicable only in conjunction with the applicable documents. Due to aerodynamic and other concerns, the application of deicing/anti-icing fluids shall be carried out in compliance with engine and aircraft manufacturers’ recommendations. The scope of training should be adjusted according to local demands. There are a wide variety of winter seasons and differences of the involvement between deicing operators, and therefore the level and length of training should be adjusted accordingly. However, the minimum level of training shall be covered in all cases. As a rule of thumb, the amount of time spent in practical training should equal or exceed the amount of time spent in classroom training.
G-12T Training and Quality Programs Committee
Navigation Measurement SoftwareTBMG-3699906/01/2020
NASA Goddard Space Flight Center has developed FlashPose, a relative navigation measurement software and VHDL for spaceflight missions requiring vehicle-relative and terrain-relative navigation and control. FlashPose processes real-time or recorded range and intensity images from 3D imaging sensors, such as LiDARs, and compares them to known models of the target surfaces to output the position and orientation of the known target relative to the sensor coordinate frame. All algorithmic processing takes place in the software application, while custom FPGA firmware interfaces directly with the Ball Vision Navigation System (VNS) LiDAR and provides imagery to the algorithm.
Air Data Computer – Minimum Performance StandardAS8002B (Current)04/28/2020
This SAE Aerospace Standard (AS) covers air data computer equipment (hereinafter designated the computer) which when connected to sources of aircraft electrical power, static pressure, total pressure, outside air temperature, and others specified by the manufacturer (singly or in combination) provides some or all of the following computed air data output signals (in analog and/or digital form) which may supply primary and/or standby flight instruments: Pressure Altitude Pressure Altitude, Baro-Corrected Vertical Speed Calibrated Airspeed Mach Number Maximum Allowable Airspeed Over-speed Warning Total Air Temperature
A-4 Air Data Subcommittee
Air Data Computer – Minimum Performance StandardAS8002B-TEST-REC (Historical)04/28/2020
This SAE Aerospace Standard (AS) covers air data computer equipment (hereinafter designated the computer) which when connected to sources of aircraft electrical power, static pressure, total pressure, outside air temperature, and others specified by the manufacturer (singly or in combination) provides some or all of the following computed air data output signals (in analog and/or digital form) which may supply primary and/or standby flight instruments: Pressure Altitude Pressure Altitude, Baro-Corrected Vertical Speed Calibrated Airspeed Mach Number Maximum Allowable Airspeed Over-speed Warning Total Air Temperature
A-4 Air Data Subcommittee
Aerospace - Passive Side Stick Unit General Requirements for Fly-by Wire Transport and BusinessARP6001B (Current)04/23/2020
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
Aerospace - Passive Side Stick Unit General Requirements for Fly-by Wire Transport and BusinessARP6001B-TEST-REC (Historical)04/23/2020
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
Automatic Pilot InstallationsARP419B (Current)04/14/2020
These recommendations cover the mechanical and electrical installation and installation test procedures for automatic pilots of the type normally used in transport type aircraft. The material in this ARP does not supercede any airworthiness requirement in the Civil Air Regulations.
A-4 Aircraft Instruments Committee
Multifunctional Structure Stabilizes and Rotates SatellitesTBMG-3636204/01/2020
Many satellites are in space to take photos. But a vibrating satellite, like a camera in shaky hands, can’t get a sharp image. Pointing it at a precise location to take a photo or perform another task is an important function that requires accuracy. Researchers have developed a way to cancel out the vibrations of a satellite by vibrating the solar panels in the opposite direction — called active noise cancellation.
Multi-Objective Flight Control Optimization FrameworkTBMG-3620103/01/2020
Composite materials are used in aerospace design because of their high strength-to-weight ratio. On modern airplanes, composite wings offer a greater degree of aerodynamic efficiency due to weight savings but at the same time introduce more structural flexibility than their aluminum counterparts. Under off-design flight conditions, changes in the wing shape due to structural flexibility cause the wing aerodynamics to be non-optimal. This effect could offset any weight-saving benefits realized by the composite wings. Structural flexibility could also cause adverse interactions with flight control and structural vibration that can compromise aircraft stability, pilot handling qualities, and passenger ride quality.
High-Performance, Piezoelectric, Hybrid Synthetic Jet ActuatorsTBMG-3618103/01/2020
NASA Langley Research Center has invented three serial high-performance, piezoelectric, hybrid synthetic jet actuators to provide active flow control for current and future wing-borne vehicles in subsonic, transonic, and supersonic flow. Effective active flow control results in reduced vehicle drag and the prevention of events that can lead to catastrophic loss.
Barometry for Altimeter CalibrationAIR1075B (Current)02/20/2020
This SAE Aerospace Information Report (AIR) is concerned only with aspects directly relating to available accuracy. While well-designed photoelectric, inductive or capacitive readers and pressure regulators, and other accessories are highly desirable for convenience and production rate, they are considered to be outside the scope of this AIR.
A-4 Aircraft Instruments Committee
Attack Reconnaissance HelicopterTBMG-3606302/01/2020
Bell Textron Inc Fort Worth, TX +1 817-280-2011
CAESAR Plug-in for MagicDrawTBMG-3598302/01/2020
The CAESAR software is a plug-in for No Magic's MagicDraw tool that allows users to capture a model of a flight system architecture at various levels of abstraction while maintaining consistency of the system design information, products, and artifacts that are commonly used in flight system design such as block diagrams that capture the system topology. Each level of abstraction is characterized by a model of components, interfaces, signals, and channels. These fundamental constructs are annotated by ontologies to provide semantics and context for architecture models at each level of abstraction. The plug-in manages consistency between models of the flight system architecture and projected views from the set of defined architecture models, and allows for annotating semantics by creating and applying metamodels that capture domain-specific concepts using the profiling mechanism in Magic-Draw. Projected views are described in specific block diagrams, tables, reports, and other
Specification Guide for Power Drive Units (PDUs)ARP5384 (Current)01/06/2020
This Recommended Practice provides a guide for specifying general design, performance, and test requirements for power drive units (PDUs) for flight controls and other applications.
A-6B3 Electro-Mechanical Actuation Committee
De-Orbit Device for SmallSatsTBMG-3570212/01/2019
To decrease de-orbit time and allow for higher-altitude orbits of small satellites, researchers at NASA and the University of Florida have developed a retractable drag device capable of modulating drag area while providing 3-axis stabilization. The device increases area without increasing mass, increasing the ability to control rotation and attitude in 12U, 15-kg CubeSats and other small satellites.
Docking System Enables Safe Rendezvous in SpaceTBMG-3561412/01/2019
Even though it has been done many times before, the docking maneuver between two objects in space is always a delicate and potentially dangerous procedure. The speed is extremely high (about 28,000 km/h in the case of the International Space Station, or ISS), and corrections are difficult. When the two objects are about to meet, maneuvering thrusters can no longer be used since their exhaust plumes can cause damage. To prevent harm, cargo transporters are caught by a robotic arm installed in the ISS and berthed manually. Manned spacecraft, on the other hand, dock directly in a computer-controlled process.
In-Service Reliability Data of Continuously Active Ball Screw and Geared Flight Control Actuation SystemsAIR5713A (Current)10/14/2019
This Aerospace Information Report (AIR) has been written to provide in-service reliability data of continuously active ball screw and geared flight control actuation systems.
A-6B3 Electro-Mechanical Actuation Committee
Lightweight Sensing and Control System for Unmanned Aerial Vehicle MonitoringTBMG-3527310/01/2019
A new sensing and control system for unmanned aerial vehicles (UAVs) allows for semi-autonomous flight. Pilots need not leave the ground to conduct routine monitoring and surveillance quickly and cost-effectively. Such systems are particularly useful during long flight segments or over remote locations, or for scientific applications such as atmospheric monitoring or crop monitoring, which might require long and repeated sampling in a specific pattern. The small, lightweight technology can be quickly adapted to a specific configuration.
Collins Aerospace provides avionics for C-130H modernization programSAE-MA-0000209/03/2019
The Lockheed C-130H Hercules fleet operated by the Air National Guard and U.S. Air Force Reserve is getting new Collins Aerospace Systems avionics that will help extend the life of the legacy aircraft by 20 years.
Kucinski, William
Rugged Network File ServersTBMG-3511709/01/2019
Ampex Data Systems Hayward, CA 650-367-2011
Aircraft Ground Deicing/Anti-Icing Training and Qualification ProgramAS6286A (Historical)06/26/2019
This document establishes the minimum training and qualification requirements for ground-based aircraft deicing/anti-icing methods and procedures. All guidelines referred to herein are applicable only in conjunction with the applicable documents. Due to aerodynamic and other concerns, the application of deicing/anti-icing fluids shall be carried out in compliance with engine and aircraft manufacturers’ recommendations. The scope of training should be adjusted according to local demands. There are a wide variety of winter seasons and differences of the involvement between deicing operators, and therefore the level and length of training should be adjusted accordingly. However, the minimum level of training shall be covered in all cases. As a rule of thumb, the amount of time spent in practical training should equal or exceed the amount of time spent in classroom training.
G-12T Training and Quality Programs Committee
Analysis and Automated Detection of Ice Crystal Icing Conditions Using Geostationary Satellite Datasets and In Situ Ice Water Content Measurements2019-01-195306/10/2019
Recent studies have found that high mass concentrations of ice particles in regions of deep convective storms can adversely impact aircraft engine and air probe (e.g. pitot tube and air temperature) performance. Radar reflectivity in these regions suggests that they are safe for aircraft penetration, yet high ice water content (HIWC) is still encountered. The aviation weather community seeks additional remote sensing methods for delineating where ice particle (or crystal) icing conditions are likely to occur, including products derived from geostationary (GEO) satellite imagery that is now available in near-real time at increasingly high spatio-temporal detail from the global GEO satellite constellation. A recent study using a large sample of co-located GEO satellite and in-situ isokinetic evaporator probe (IKP-2) total water content (TWC) datasets found that optically thick clouds with tops near to or above the tropopause in close proximity (≤ 40 km) to convective updrafts were most
Bedka, Kristopher, Yost, Christopher, Nguyen, Louis, Strapp, J. Walter, Ratvasky, Thomas, Khlopenkov, Konstantin, Scarino, Benjamin, Bhatt, Rajendra, Spangenberg, Douglas, Palikonda, Rabindra
Flight Control Actuators - Dynamic Seals, Collection of Duty Cycle DataARP4895B (Current)05/16/2019
This SAE Aerospace Recommended Practice (ARP) provides an algorithm aimed to analyze flight control surface actuator movements with the objective to generate duty cycle data applicable to hydraulic actuator dynamic seals.
A-6A3 Flight Control and Vehicle Management Systems Cmt
UAV Ground Control StationTBMG-3432805/01/2019
General Atomics Aeronautical Systems, Inc. San Diego, CA 858-762-6700
Attitude Control of the Vehicle with Six In-Wheel Drive and Adaptive Hydro Pneumatic Suspensions2019-01-045604/02/2019
The ability of actively adjusting attitude provides a great advantage for those vehicles used in special environments such as off-road environment with extreme terrains and obstacles. It can improve vehicles’ stability and performance. This paper proposes an attitude control system for realizing the active attitude adjustment and vehicle motion control in the same time. The study is based on a vehicle with six wheel independent drive and six independent suspensions (6WIDIS), which is a kind of unmanned vehicle with six in-wheel drives and six independent hydro pneumatic suspensions. With the hydro- pneumatic suspensions, the vehicle’s attitude can be actively adjusted. This paper develops a centralized- distributed control strategy with attitude information obtained by multi-sensor fusion, which can coordinate the complex relationship among the six wheels and suspensions. The attitude control system consists of three parts. The first part is the attitude determination that includes
Li, Boxin, Zheng, Gangtie, Wang, Zhaokui
Automated 6DOF Model Generation and Actuator Sizing within AFSIM2019-01-133603/19/2019
The Air Force Research Laboratory has interest in automatically generating the extensive aerodynamic databases essential for six degree of freedom (6DOF) models and the use of 6DOF models for design. To be most useful, automation must include all aspects of producing the database including meshing, control surface deflections, running the CFD solution, and storage of the results. This effort applies newly-developed software to produce the desired results. Firstly, AFRL software called Computational Aircraft Prototype Syntheses (CAPS) allows automated meshing using the Advancing Front Local Reconnection (AFLR) software from Mississippi State University1 and automated control surface deflection using Engineering Sketch Pad (ESP) software from MIT/Syracuse. CAPS includes the ability to run the NASA CFD code FUN3D and interpret the FUN3D results via an Application Interface Module (AIM). This may sound like a complicated process. However, it is quite simple using a python interface to CAPS
Allison, Darcy, Shimmin, Kyle, Schley, William, Bryson, Dean
An Open Source Domain-Specific Avionics System Architecture Model for the Design Phase and Self-Organizing Avionics2019-01-138303/19/2019
State-of-the-art avionics systems are standardized, e.g. the computing system of the flying vehicle is composed of pre-defined and pre-qualified modules of a standardized avionics platform. Integrated Modular Avionics (IMA) is the most popular representative, but not the only one. Two challenges of standardized avionics platform are system design and configuration. Since the high numbers of functions, modules, and constraints for modern air vehicles, bringing up the optimal system architecture is a difficult job if carried out manually. The subsequent process of creating millions of configuration parameters is time consuming and error prone. Both issues are similar and are, in general, processable by algorithms. Algorithms proved to provide significant support for current system design issues and might be mandatory in future, when avionics become self-organizing and the design and configuration are derived by the platform itself. Automated design already proved its advantages and self
Annighoefer, Bjoern
Streamlining EMC Solutions for Avionics Interfaces19AERP02_0402/01/2019
Lightning strikes to jet airliners are common - about once every 1000 flight hours. The DO-160G standard, Environmental Conditions and Test Procedures for Airborne Equipment, is a standard for the environmental testing of avionics hardware. Many airplane manufacturers specify DO-160G Section 22, lightning induced transient susceptibility, as a requirement for critical systems like guidance, radars, communications, engine control, and heat and air controls. Aircraft fuselage, wing and tail flight controls, wing tips, fin tips, engine nacelles, and landing gear are the areas most likely to be hit by lightning strikes. Modern aircraft are designed with fly by wire systems for flight controls. Fly by wire means that inputs from either flight control computers or pilot manual inputs are transmitted electrically to a servomotor, which controls flight control actuators. Communication interfaces for these flight control systems can be implemented on an RS-485 physical layer. Communication
Streamlining EMC Solutions for Avionics InterfacesTBMG-3377302/01/2019
Lightning strikes to jet airliners are common - about once every 1000 flight hours. The DO-160G standard, Environmental Conditions and Test Procedures for Airborne Equipment, is a standard for the environmental testing of avionics hardware. Many airplane manufacturers specify DO-160G Section 22, lightning induced transient susceptibility, as a requirement for critical systems like guidance, radars, communications, engine control, and heat and air controls. Aircraft fuselage, wing and tail flight controls, wing tips, fin tips, engine nacelles, and landing gear are the areas most likely to be hit by lightning strikes.
Evaluation of Aeronautical Design Standard – 33 Using a UH-60A Black HawkTBMG-3376402/01/2019
In 1982, the U.S. Army Aeroflightdynamics Directorate (AFDD), then assigned under the U.S. Army Aviation Systems Command (AVSCOM), began development of a new handling qualities specification for military rotorcraft. This effort resulted in the U.S. Army's initial Aeronautical Design Standard–33 (ADS-33A), “Handling Qualities Requirements for Military Rotorcraft,” published in May 1987. It was initially applied to the RAH-66 Comanche Helicopter program, meaning the handling qualities requirements generally related more to scout and attack classes of rotorcraft. As more data became available and lessons learned emerged from using ADS-33A, refinements were implemented into ADS-33B and ADS-33C).
Evaluation of Aeronautical Design Standard - 33 Using a UH-60A Black Hawk19AERP02_0902/01/2019
Flight tests determine whether performance standards developed for scout and attack class rotorcraft can be applied to utility helicopters. Army Research, Development, and Engineering Command, Redstone Arsenal, Alabama In 1982, the U.S. Army Aeroflightdynamics Directorate (AFDD), then assigned under the U.S. Army Aviation Systems Command (AVSCOM), began development of a new handling qualities specification for military rotorcraft. This effort resulted in the U.S. Army's initial Aeronautical Design Standard-33 (ADS-33A), “Handling Qualities Requirements for Military Rotorcraft,” published in May 1987. It was initially applied to the RAH-66 Comanche Helicopter program, meaning the handling qualities requirements generally related more to scout and attack classes of rotorcraft. As more data became available and lessons learned emerged from using ADS-33A, refinements were implemented into ADS-33B and ADS-33C). In 1990, ADS-33C was assessed using an AH-64A Apache by the U.S. Army's
Ray Optics Simulation of Inertial Navigation SystemsTBMG-3328511/01/2018
Attitude detection is a crucial element in aircraft and spacecraft navigation. The motion of an aircraft consists of a translational component (motion of its center of mass with respect to the Earth) and a rotational component (rotation of the aircraft around its center of mass). Attitude detection is the measurement of the rotational component of the aircraft's motion, and depending on the mission this measurement might need to be extremely accurate. Advances in computer simulation technology have made it easier than ever to set up high-fidelity numerical simulations of inertial navigation and attitude control systems of the type typically found aboard aircraft and spacecraft.
Analysis of the Effects of Modeling Depth and Parameter Uncertainties on the System Behavior of a Multifunctional High Lift Actuation System2018-01-191810/30/2018
Modeling and simulation have become an important aspect of the design and development process of aircraft systems. During the design of high lift actuation systems for example, the dynamic loads in the transmission are estimated by simulation. Nevertheless huge development efforts and financial resources are still invested in physical testing. These integration and testing phases take place at a late stage in the design process. Therefore, identified malfunctions and development errors lead to undesired iterations and thus to high costs as well as to an increased development time. This issue is emphasized as system complexity is rises continuously in conjunction with an increase in the number of interconnections and functionality. Hence, early and continuous virtual testing activities on the overall system level become increasingly important. In order to establish such a process, this paper analyzes the effects of modeling depth and parameter uncertainties on the overall system
Schäfer, Andreas, Schmid, Michael
A Methodology for Formal Requirements Validation and Automatic Test Generation and Application to Aerospace Systems2018-01-194810/30/2018
Automation on Validation and Verification (V&V) leveraging Formal Methods, and in particular Model Checking, is seeing an increasing use in the Aerospace domain. In recent years, Formal Methods have been used to verify systems and software and its correctness as a way to augment traditional methods relying on simulation and testing. Recent updates to the relevant Aerospace regulations (e.g. DO178C, DO331 and DO333) now have explicit provisions for utilization of models and formal methods. In a previous paper a compositional methodology for the verification of Aerospace Systems has been described with application to Electrical Power Generation and Distribution Systems. In this paper we present an expansion of the previous work in two directions. First, we describe the application of the methodology to the validation of Proximity Sensing Systems (PSS) requirements showing the effectiveness of the method to a new aerospace domain. Second, both the methodology and technology components
Ferrante, Orlando, Scholte, Eelco, Rollini, Simone, North, Rob, Manica, Luca, Senni, Valerio
An Integrated Approach to Model Based Engineering with SysML, AADL and FACE2018-01-194210/30/2018
Multiple model-based engineering (MBE) frameworks have emerged to cover the many requirements for the engineering of avionics systems: from early requirement capture to the final system and embedded software generation, through refinement and V&V activities. In this paper, we consider the SysML, AADL and FACE standards. They are promoted by different standardization bodies, with different objectives. We note they are often seen as competitive, while we argue it is the opposite: there is a potential for a synergistic coupling. To date, no complete open evaluation on the feasibility of such capability has been done. In this paper, we present one workflow that illustrates the joint use of SysML, AADL and FACE. We consider a basic flight control system to exercise the proposed process and gateways between the three notations. We use SCADE Architect by ANSYS that supports the three notations in a unified workbench to illustrate refinement scenarios from one notation to another, then
Zhe, Wang, Hugues, Jerome, Chaudemar, Jean-Charles, LeSergent, Thierry
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
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