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The dynamic model is built in Siemens Simcenter Amesim platform and simulates the performances on track of JUNO, a low energy demanding Urban Concept vehicle to take part in the Shell Eco-Marathon competition, in which the goal is to achieve the lowest fuel consumption in covering some laps of a racetrack, with limitations on the maximum race time. The model starts with the longitudinal dynamics, analysing all the factors that characterize the vehicle’s forward resistance, like aerodynamic forces, altimetry changes and rolling resistance. To improve the correlation between simulation and track performances, the model has been updated with the implementation of a Single-Track Model, including vehicle rotation around its roll axis, and a 3D representation of the racetrack, with an automatic trajectory following control implemented. This is crucial to characterise the vehicle’s lateral dynamics, which cannot be neglected in simulating its performances on track.

The electronics package for a Category II qualified business jet aircraft and the function of the various components of the system are described. These components include: dual Collins 51-RV-l VOR/ILS/G. S. receivers which provide and utilize beams along which the aircraft descends for a safe approach; a Collins AL-101 radio altimeter to determine altitude; dual flight directors for automatic and manual approaches; and a Collins 54W-1 comparator warning system, to name a few. A general rather than a technical approach is used.

Switching controls are those that can switch between control or plant modes to perform their functions. They have the advantage of being simpler to design than an equivalent control system with a single mode. However, the transients between those modes can introduce steps or overshootings in the state variables, and this can degrade the performance or even damage the control or the plant. So, the smoothing of such transients is vital for their reliability and mantainability. This is can be of extreme importance in the aerospace and automotive fields, plenty of switchings between manual and autopilot modes via relays, or among gears via clutches, for example. In this work, we present a first strategy for smoothing transients in switching controls of aerospace and automotive systems.

Milestones of domestic air transportation in the past 50 years are highlighted. Many early innovations were of European origin. Lindbergh’s flight accelerated the use of airplanes as a means of domestic transportation. The DC-3, prior to World War II, achieved a high degree of standardization and established a foundation for future airline growth. After World War II, converted military transports were primary means of conveyance. Phenomenal growth of air travel is due to increased speed, safety, and comfort brought about by use of four-engine planes, automatic pilot, cabin pressurization, and improvements in electronic guidance systems. Basic problems such as over-capacity, need for greater standardization, better ground facilities, and efficient servicing of local air traffic face the airlines today.

This document is intended to establish preferred abbreviations for terms used on panels, controls, displays, instruments, placards, and markings. The recommendations apply to equipment used by crew members in the flight deck of transport aircraft. The abbreviations, acronyms, and symbols do not supersede those used in airworthiness regulations or aeronautical charts or other aircraft documents.

No Scope available.

General terms peculiar to aerospace fluid power and control systems are defined in this glossary. Relevant terms have been excerpted from the referenced documents and included herein from the aerospace terms felt to be most useful to the ISO. This is a systems document and the only component-related terms are those significant at the systems level.

No scope available.

No scope available.

AIR 1873 is being issued by the SAE E-32 committee on Aircraft Gas Turbine Engine Monitoring. It provides guidance on the specification, application and use of a Limited Engine Monitoring System which is defined as an EMS where the measurement parameters are ussually limited to those that are provided as part of the standard aircraft instrumentation.

This Aerospace Standard covers an air data computer characterized by the concept of transducing and computing the majority of air data requirements for an aircraft. The display instruments and other using subsystems are not considered in this scope except where they perform computing operations for output parameters as covered by this specification. The computer may accept the inputs and provide the outputs listed in paragraphs 2.1 and 2.2 respectively. The computer may also provide an altitude encoder output for IFF Mark X ¯ ¯ (SIF)/Air Traffic Control Radar Beacon System SIF/ATCRBS; in which case AS 855* "Altitude Device Providing Outputs for Automatic Pressure Altitude Reporting" shall be referred to for applicable minimum standards. (Note - Reference to air data computer in subsequent paragraphs will be designated as "instrument".)

This standard defines mechanical dimensions and thermal standards for aircraft indicators and displays. Thermal interface data is included for indicators and their operating environment. These indicators may be stand alone or part of larger integrated display system. This standard defines mechanical dimensions and thermal standards for aircraft indicators and displays. Thermal interface data is included for indicators and their operating environment. These indicators may be stand alone or part of larger integrated display system.

This document recommends criteria for Airborne Wake Vortex Information Systems, including operational objectives, characteristics, and functional requirements. The recommendations in this document apply to transport aircraft, and describe the operational objectives of wake vortex information systems, situational displays, guidance systems, and avoidance/detection systems.

This document recommends criteria for Airborne Windshear Systems, including operational objectives, characteristics and functional requirements. The recommendations of this document apply to transport aircraft, and describe the operational objectives of Windshear warning devices, situational displays, guidance systems and detection/avoidance systems.

This document establishes the minimum criteria for ground based aircraft deicing/anti-icing with fluids to ensure the safe operation of aircraft during icing conditions. This document does not specify requirements for particular airplane models.

This document establishes the minimum criteria for ground based aircraft deicing/anti-icing with fluids to ensure the safe operation of aircraft during icing conditions. This document does not specify requirements for particular airplane models.

This document provides information to assist in the preparation of particular airline aircraft ground deicing/anti-icing procedures and to ensure safe operation of large transport aircraft during adverse conditions conducive to aircraft icing on the ground, in accordance with aircraft manufacturers’ recommendations.

This AS covers __________ which measure and display __________ or This AS covers __________ basic types of (no capitals) instruments as follows: Note: Each type number to be followed by a brief description as it would if the scope were covering only a single type. As many types as required may be used.