Browse Topic: Flight guidance systems

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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-TEST-REC (Historical)11/03/2020
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
G-10 Executive Advisory Group
Human Engineering Recommendations for Data Link SystemsARP4791B (Current)11/03/2020
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
G-10 Executive Advisory Group
Flight Deck Lighting for Commercial Transport AircraftARP4103A (Current)09/17/2019
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
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
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
MULTI-MODE RECEIVER (MMR) - DIGITALARINC755-5 (Current)01/25/2018
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
Autopilot, Flight Director, and Autothrust SystemsARP5366 (Current)01/04/2017
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
Aircraft Flight Control Systems DescriptionsAIR4094A (Current)07/18/2016
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
Simulation-Driven Methodology for the Requirements Verification and Safety Assessment of Innovative Flight Control Systems2015-01-247809/15/2015
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
Kreitz, Tobias, Bornholdt, Riko, Krings, Matthias, Henning, Karsten, Thielecke, Frank
Air-Ground Communications System Aims to Make Flying SaferTBMG-2229806/01/2015
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.
ACTIVE SAFETY STARTS IN THE PILOT'S SEAT14MOMP02_0302/01/2014
Dassault Aviation's next-generation integrated digital avionics systems contribute to enhanced air safety in civil applications. As the basic configuration of any new business jet is likely to differ little in comparison to rival airplanes, the key to making a significant leap forward in technology while offering a competitive advantage is to be found beneath the skin, rather than in its shape. Increased safety is paramount in any new aircraft program, and modern digital avionics has considerably eased the pilot workload over the years, though the sheer quantity of data that is available in flight now brings additional challenges in the cockpit.
Gardner, Richard
Active safety starts in the pilot's seat14AERD01_0101/15/2014
Dassault Aviation's next-generation integrated digital avionics systems contribute to enhanced air safety in civil applications. As the basic configuration of any new business jet is likely to differ little in comparison to rival airplanes, the key to making a significant leap forward in technology while offering a competitive advantage is for the immediate future always going to be found beneath the skin, rather than in its shape. Increased safety is paramount in any new aircraft program, and modern digital avionics has considerably eased the pilot workload over the years, though the sheer quantity of data that is available in flight now brings additional challenges in the cockpit.
Gardner, Richard
Small Airplane Considerations for the Guidelines for Development of Civil Aircraft and Systems2013-01-223309/17/2013
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
Voros, Robert E.
Bob Reisse, ALHAT Project Manager, Langley Research Center, Hampton, VA.TBMG-1601303/01/2013
Bob Reisse coordinates the design and testing of ALHAT (Autonomous Landing Hazard Avoidance Technology) sensors. In December, ALHAT instruments were melded to HUEY helicopters, which used sensors and an integrated computer system to provide guidance and assist pilots. The technology will also enable landing near specific resources and locations across the solar system, including the moon, Mars, and other asteroids.
Automatic PilotsAS402C (Current)08/22/2012
This Aeronautical Standard covers Automatic Pilots intended for use on aircraft to automatically operate the aerodynamic controls to maintain flight and/or to provide maneuvering about the three axes through servo control.
A-4 Aircraft Instruments Committee
MULTI-MODE RECEIVER (MMR)-DIGITALARINC755-4 (Current)06/30/2010
This document defines an ILS/MLS/GLS multi-mode receiver that provides the flight path deviation guidance to the aircraft during the final approach and landing phase. The data sources may be Instrument Landing System (ILS), Microwave Landing System (MLS) or GNSS Landing System (GLS). Supplement 4 adds ILS look-alike data (ARINC 429) in support of GLS CAT II/III operation. It also defines Final Approach Segment Data Messages (FASDM) input labels to the MMR for new aircraft.
Airlines Electronic Engineering Committee
Aircraft Level Steering Runaway Failure Analysis2009-01-313611/10/2009
Integration of aircraft landing gear systems requires a high level of knowledge and understanding of these systems and how they contribute to aircraft performance. This paper considers a specific design requirement for the steering system. Failure of the steering system, resulting in the aircraft leaving the runway at high speed, can be considered hazardous or even catastrophic. The ability of the system to detect such a failure and take appropriate action is a key aspect of the design. This paper describes an aircraft level steering runaway failure analysis using an aircraft level mechanical and hydraulic control coupled simulation model. The aircraft level simulation model includes aircraft structure, weight and inertia. Appropriate loads and forces (engine thrust, aerodynamic forces, lift, drag) and moments are then applied. The model also includes nose and main landing gears, brakes and tires. The steering system model includes all hydraulic and control components, with failure
Wang, Phillip, Dacko, Les, Keller, Nicolas, Wu, Jiangning
NAVIGATION SYSTEMS DATABASEARINC424-19 (Current)12/19/2008
THE CURRENT VERSION OF THIS DOCUMENT IS 424-21. THIS PREVIOUS VERSION IS AVAILABLE FOR YOUR CONVENIENCE. This standard provides a data base comprising standards used for the preparation of a navigation system data base. This data may be used with the operational flight software in a wide range of navigational equipment.
Airlines Electronic Engineering Committee
HUMAN ENGINEERING RECOMMENDATIONS FOR DATA LINK SYSTEMSARP4791A (Historical)02/16/2008
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
G-10 Executive Advisory Group
DATA LINKARP4102/13A (Current)07/11/2007
This document recommends criteria for a system designed to manage and communicate information via data link to support flight operations.
S-7 Flight Deck Handling Qualities Stds for Trans Aircraft
Airborne Windshear SystemsARP4102/11C (Current)07/11/2007
This document recommends criteria for Airborne Windshear Systems, including operational objectives, characteristics, and functional requirements. The recommendations in this document apply to transport aircraft, and describe the operational objectives of windshear alerting systems, situational displays, guidance systems, and avoidance/ detection systems.
S-7 Flight Deck Handling Qualities Stds for Trans Aircraft
Design Objectives for Handling Qualities of Transport AircraftARP4104 (Current)07/11/2007
This document specifies the requirements for the design objectives for handling qualities applicable to transport aircraft operating in the subsonic, transonic, and supersonic speed range. These objectives are not necessarily applicable to rotor or VTOL aircraft.
S-7 Flight Deck Handling Qualities Stds for Trans Aircraft
Final Approach Spacing System (FASS)ARP5628 (Current)11/28/2005
This document recommends criteria and requirements for a Final Approach Spacing System (FASS) for transport aircraft. This is an Aerospace Recommended Practice to support the development of a Final Approach Spacing System (FASS) for Approach Spacing for Instrument Approaches (ASIA) operations.
S-7 Flight Deck Handling Qualities Stds for Trans Aircraft
424-18 Navigation Systems Data BaseARINC424-18 (Historical)11/23/2005
THE CURRENT VERSION OF THIS DOCUMENT IS 424-22. THIS PREVIOUS VERSION IS AVAILABLE FOR YOUR CONVENIENCE. This standard provides a data base comprising standards used for the preparation of a navigation system data base. This data may be used with the operational flight software in a wide range of navigational equipment.
Airlines Electronic Engineering Committee
Summary of NASA's Extreme Short Take-Off and Landing (ESTOL) Vehicle Sector Activities2005-01-314510/03/2005
NASA is exploring a research activity to identify the technologies that will enable an Extreme Short Take-Off and Landing (ESTOL) aircraft. ESTOL aircraft have the potential to offer a viable solution to airport congestion, delay, capacity, and community noise concerns. This can be achieved by efficiently operating in the underutilized or unused airport ground and airspace infrastructure, while operating simultaneously, but not interfering with, conventional air traffic takeoffs and landings. Concurrently, the Air Force is exploring ESTOL vehicle solutions in the same general performance class as the NASA ESTOL vehicle to meet a number of Advanced Air Mobility missions. The capability goals of both the military and civil vehicles suggests synergistic technology development benefits. This paper presents a summary of the activities being supported by the NASA ESTOL Vehicle Sector.
Zuk, John, Wardwell, Douglas A.
Real-Time Simulation of Aeroheating the Hyper-X AirplaneTBMG-16801/01/2005
A capability for real-time computational simulation of aeroheating has been developed in support of the Hyper-X program, which is directed toward demonstrating the feasibility of operating an air-breathing ramjet/scramjet engine at mach 5, mach 7, and mach 10. The simulation software will serve as a valuable design tool for initial trajectory studies in which aerodynamic heating is expected to exert a major influence in the design of the Hyper-X airplane; this tool will aid in the selection of materials, sizing of structural skin thicknesses, and selection of components of a thermal-protection system (TPS) for structures that must be insulated against aeroheating.
NAVIGATION SYSTEM DATA BASEARINC424-17 (Current)08/31/2004
THE CURRENT VERSION OF THIS DOCUMENT IS 424-21. THIS PREVIOUS VERSION IS AVAILABLE FOR YOUR CONVENIENCE. This standard provides a data base comprising standards used for the preparation of a navigation system data base. This data may be used with the operational flight software in a wide range of navigational equipment.
Airlines Electronic Engineering Committee
An eye on UAVsAEROAUG03_0408/01/2003
Electronics play an important role in unmanned aerial vehicles designated for intelligence, surveillance, and reconnaissance mission areas, as well as for combat. Roadmaps seem to be everywhere these days. Earlier this year, Dyke Weatherington, Deputy, Office of the Secretary of Defense, Unmanned Aerial Vehicle Planning Task Force, announced the release of the 2002 Unmanned Aerial Vehicle Roadmap. According to Weatherington, one of the specific purposes of the document, which looks out to 2027, is to identify “those near-term mission areas that can be impacted significantly by emerging UAV technology.” Another goal for the roadmap is its use as “a guide to our industry and allies, identifying the highest value areas for independent investment and areas for international cooperation,” said Weatherington. Ironically, it is international uncooperation that has made UAVs increasingly important for a wide range of armed forces mission scenarios-particularly ISR, or intelligence
Broge, Jean L.
Dassault adds another FalconAEROAPR02_0404/01/2002
The Falcon 7X features a host of new technologies, including an advanced wing design, making it Dassault's next-generation business jet. Announced at last year's Paris Air Show, the Falcon 7X will become Dassault Falcon Jet Corp.'s newest addition to its business jet product line. The number seven launches a new naming convention for the company's new generation of Falcons, with the X tag denoting the advanced technology aspects of the airplane. Key to the aircraft's technology is its all-new wing design, which features a planform 44% larger in area than that of the Falcon 900EX and an aspect ratio of 9.0 compared to 7.6. “Dassault's goal was to optimize the wing's total shape (airfoil and planform) in ways that allow structural simplification, weight and cost savings, and a generous internal volume for fuel-all while maintaining the inherently safe and pilot-friendly flying qualities traditional within the Falcon family,” said Olivier Villa, Vice President of Falcon Programs.
Automatic PilotsAS402B (Historical)07/01/2001
This Aeronautical Standard covers Automatic Pilots intended for use on aircraft to automatically operate the aerodynamic controls to maintain flight and/or to provide maneuvering about the three axes through servo control.
A-4 Aircraft Instruments Committee
Costs and Benefits of Head up Displays: An Attention Perspective and a Meta Analysis2000-01-554210/10/2000
This paper reports a meta analysis of all studies located in the literature that have compared head up versus head down display of equivalent information, as these displays support both tracking (e.g., flight path control) and discrete event detection. The data clearly indicate a HUD advantage for most tasks, except tracking during cruise flight and event detection during final approach. The latter HUD cost however is observed only when events to be detected are entirely unexpected, reflecting a form of cognitive tunneling. The meta-analysis also reveals an advantage for conformal over non-conformal HUD imagery.
Fadden, Steven, Wickens, Christopher D., Ververs, Patricia
Staying Ahead of the Automation: A Vertical Situation Display Can Help2000-01-561410/10/2000
In this paper we present a Vertical Situation Display (VSD) for Flight Management System equipped aircraft. It was developed, implemented and evaluated in the Advanced Concepts Flight Simulator at NASA Ames Research Center. The VSD was designed to support flight crews in managing the vertical flight path when using high levels of aircraft automation inside Terminal Areas.
Prevot, Thomas, Palmer, Everett
Human Factor Issues Associated with HUD-Based Hybrid Landing Systems: SEXTANT’s Experience1999-01-551210/19/1999
HUD-based hybrid landing systems developed by SEXTANT Avionics have been successfully certified for AEROPOSTALE and ALITALIA. The philosophy of such system is to offer minima reductions (down to DH 35 ft and RVR 125 m) with automatic Cat 3A operations. From a human factors stand point, the basis of such an approach is that improved situational awareness provided by the HUD allows to maintain an acceptable safety level for operations despite lower DH and visibility. Though, it is well known that switching from a supervisory control mode to a manual control mode under time pressure is a very serious challenge for the human operator. In this regard, numerous human factors issues were addressed during the concept validation phase and results applied to certification. This was particularly true for difficult exercises , as manual go around at DH with one engine out on the B-737, where it had to be demonstrated that specific information provided in the HUD allowed to keep an acceptable level
Audrezet, H., Alba, P.
Flight Simulation and Aeronautical Education - Ten Years of Experience97563510/01/1997
The inclusion of flight simulation into the undergraduate aeronautical engineering curriculum has been a major goal at the U.S. Air Force Academy during the past ten years. Specifically, flight simulation has been used in four flight mechanics/design courses with excellent results. Junior and senior-level aeronautical engineering students are provided the opportunity to “fly” and evaluate a variety of aircraft configurations and flight situations. This paper reviews simulation projects that are used in each of the four courses and highlights lessons learned over the past ten years. The integration of flight simulation into these courses has been very effective as an educational tool and has become a strength of our “hand-on” program.
Yechout, Thomas R., Morris, Steven L.
Development of an Interactive Computerized Aircraft Design System96552910/01/1996
During the last decades a great number of new technologies have been developed to increase the efficiency and safety of new aircraft. Many of these technologies demand, however, a completely different design philosophy, design approach and organization of the design process. At the same time the fast growing capacity of modern computer systems has opened up the possibility of more accurate design and analysis, interactive design, design optimization and strategic design management. In many cases this has led to a complete reconsideration and reorganization of the entire design process. In order to keep pace with these developments and to be able to make a contribution to future developments in this field the ICADS Interactive Computerized Aircraft Design System was set up. This system must enable us to make students and designers familiar with advanced design methods and the logic behind it. This paper describes the causes and reasons for the lay-out of the system as well as the design
Seffinga, B. F.
AUTOMATIC PILOTS (Turbine Powered Subsonic Aircraft)AS440A (Historical)09/01/1996
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
Development of the McDonnell Douglas MD-9095205209/01/1995
Douglas developed the MD-90, an IAE V2500-powered derivative of the MD-80, to satisfy a customer need for a more environmentally - friendly 150-seat, short/medium range jet transport. The program was launched in late 1989 with requirements to: significantly reduce community noise and engine emissions improve aircraft fuel efficiency make other technical improvements where cost effective for the customer. The aircraft was certificated in November 1994 and entered airline service in April 1995. The MD-90 meets all of its technical requirements.
Kressly, Arthur E., Parker, Anthony C.
FLIGHT MANAGEMENT SYSTEM (FMS)ARP4102/9 (Historical)05/01/1995
This document recommends criteria and requirements for a Flight Management System (FMS) for transport aircraft.
S-7 Flight Deck Handling Qualities Stds for Trans Aircraft
Improved Operational Reliability and Safety with HUD - The Alaska Airlines Experience94211410/01/1994
This paper relates the experience of Alaska Airlines in the acquisition and operation of the Heads Up Display (HUD) on it's fleet of 23 Boeing 727-200 aircraft. The airline has accrued more than five years of successful experience with the system since it's first installation in late 1987. In using this system for approaches to Category IIIa (Cat IIIa) weather minimums, Alaska differs from most prior HUD users in that the approaches are flown and landed manually, as opposed to the more common use of the HUD to monitor the autopilot during a coupled, autoland approach.
Kaiser, Kim J.
Flight Deck Automation: Problems and Concerns as Reported in the Aviation Safety Reporting System94209410/01/1994
Aviation Safety Reporting System (ASRS) reports were analyzed to identify flight deck operational problems related to aircraft automation systems, particularly those problems that may be exacerbated by the addition of data link systems. Four major automation problem groups were discovered (Automation Failure, Programming Errors, Distraction- Programming, and Mismanagement-Confusion). Also, several automation-induced errors were identified (e.g., runway incursions and altitude deviations). The reports are classified by attributes such as automation system and flight error. Each automation group is discussed, and based on a limited sample of reports, conclusions are drawn; with respect to data link, potential positive and negative impacts are described.
Reynolds, Michael, Neumeier, Mark, Mitman, Robert
Flight Path Control for the Approach and Landing of the Quiet STOL Experimental Aircraft ASKA94000103/01/1994
The Upper Surface Blowing STOL experimental aircraft ASKA, was developed and flight tested by the National Aerospace Laboratory of Japan. The ASKA operated well on the backside of the drag curve, and because of this flight path control was accomplished with the throttle lever (thrust) during approach and landing. To compensate for the sluggish flight path response caused by the thrust response lag, the flight path control law put in stability and control augmentation system. Flight tests were conducted to evaluate flight path and airspeed response characteristics. This paper describes ASKA's flight path and airspeed response characteristics, as well as construction of the flight path control system.
Okada, Noriaki
In-Flight Simulator Evaluation of a Flight Reference Display for Powered-Lift STOL Aircraft94001303/01/1994
A new flight reference display for powered-lift STOL aircraft was proposed and evaluated in actual flight environment. The display was developed to provide a simple monitoring system of STOL safety margins with good handling characteristics in place of a speed indicator. Using this display, pilots repeated simulated approaches of the experimental jet STOL “ASKA” using the VSRA as an in-flight simulator. In the evaluation, emphasis was placed on agreement between the display and the motion cues experienced by the pilot. Pilot comments and flight data confirmed satisfactory control characteristics and safety margin presentation of the display.
Tanaka, Keiji, Funabiki, Kohei, Terui, Yushi, lnagaki, Toshiharu
Flying Qualities Development and Flight Simulation Evaluation of the TW-68 Tilt-Wing VTOL Aircraft93251709/01/1993
The TW-68 is a civil tilt-wing aircraft proposed by the Ishida Group. Flight simulation was applied to develop the flying qualities of this design. The simulation was accomplished using a mathematical model specially created for this purpose. The effort culminated in piloted evaluations of the simulated aircraft's flight characteristics in a variety of representative mission tasks, both with and without the augmentation of a core Automatic Flight Control System. The paper describes the mathematical model, simulation experiments and results. Flight control laws and their development are also discussed, as are the predicted flight capabilities and limitations of the TW-68.
Kimball, Dwayne F.
Airborne Windshear SystemsARP4102/11B (Historical)06/29/1993
This document recommends criteria for Airborne Windshear Systems, including operational objectives, characteristics, and functional requirements. The recommendations of the document apply to transport aircraft, and describe the operational objectives of windshear alerting systems, situational displays, guidance systems, and avoidance/detection systems.
S-7 Flight Deck Handling Qualities Stds for Trans Aircraft
Concepts for Aircraft Subsystem Integration93137704/01/1993
The Air Force has an initiative entitled, Subsystem Integration Technology (SUIT) to develop and demonstrate integration technology as applied to the traditional aircraft utility subsystems. Utility subsystems perform functions such as auxiliary power generation, environmental control, and fuel management. Commonly these different subsystems are developed independently and then interfaced when building a particular flight vehicle. The SUIT program considers all functions accomplished by the traditional utility subsystems to be responsibilities of a single entity called a utility suite. This suite is designed with overall vehicle level performance objectives rather than trying to maximize the performance of individual functions and is not bound to maintaining the traditional allocation of functions among the hardware labeled as fuel management, environmental control, or secondary power. The SUIT program has the objective of developing and demonstrating design data and assessment
Burkhard, Alan H., Haskin, William L.
MMW Technology For Enhanced Situation Awareness/Enhanced Vision Systems92192910/01/1992
Airline operations today can be adversely affected by low visibility weather. When fog conditions occur, airlines are limited to certain operating minimums for landing and takeoff. Millimeter wave (MMW) radar systems are now demonstrating the ability to see in fog. Providing the pilot with a system to see through the fog may result in FAA certification to lower landing and takeoff minimums. This paper discusses the use of MMW radar technology to provide pilots with enhanced vision and enhanced situation awareness.
Selogie, Mark L.
HUD Guidance for the ASKA Experimental STOL Aircraft using Radar Position Information92104104/01/1992
The paper describes a high performance Head-Up Display (HUD) guidance system installed on the experimental powered-lift STOL aircraft “Aska”. Since the maiden flight in October, 1985, the HUD system has been used in all the flight tests. The HUD has an accurate flight path symbol generated by inertial velocity from the IRS which is updated by up-linked precision radar position data. The flight path symbol is very useful for precise approach and flare control for Aska which has large ground effects. A synthetic runway is also presented, which is conformal with the real runway, using the position data from the ground tracking radar system. Under Instrument Meteorological conditions (IMC), the pilot can approach and land using the HUD synthetic runway as well as in Visual Meteorological Conditions (VMC). The HUD system proved to be a valuable aid to the pilot for all the Aska flight tests. A NASA Ames Research Center test pilot demonstrated touch down accuracy of less than 8 meters (peak
Yazawa, Kenji, Terui, Yushi
Results and Lessons Learned from the STOL & Maneuver Demonstration Program91200509/01/1991
The STOL and Maneuver Technology Demonstrator (S/MTD) Program has validated a set of technologies that give a supersonic fighter all-weather Short Takeoff and Landing (STOL) performance while also enhancing up-and-away maneuverability. Significant reductions in both takeoff and landing distances, compared with the unmodified F-15, have been measured. The additional pitch control power of thrust vectoring has been demonstrated up to 30° angle of attack. The effectiveness of up-and-away reversing has been identified. First, major flight test results are presented and then lessons learned from this integration program are discussed.
Moorhouse, David J., Laughrey, James A.
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