Browse Topic: Pitot-static instruments
This SAE Aerospace Information Report (AIR) relates considerations for design test procedures and test data evaluation for qualification of tire spray deflection devices
This SAE Aerospace Standard (AS) covers the following basic types: Type I - Pitot pressure, straight and L-shaped, electrically heated. Type II - Pitot and static pressures, straight and L-shaped, electrically heated
This SAE Aerospace Standard (AS) specifies minimum performance requirements for pressure altimeter systems other than air data computers. This document covers altimeter systems that measure and display altitude as a function of atmospheric pressure. The pressure transducer may be contained within the instrument display case or located remotely. Requirements for air data computers are specified in AS8002. Some requirements for nontransducing servoed altitude indicators are included in AS791. This document does not address RVSM requirements because general RVSM requirements cannot be independently detailed at the component level. The instrument system specified herein does not include aircraft pressure lines. Unless otherwise specified, whenever the term “instrument” is used, it is to be understood to be the complete system of pressure transducer components, any auxiliary equipment, and display components. The test procedures specified herein apply specifically to mechanical type
This SAE Aerospace Recommended Practice (ARP) applies to Point-Of-Use, Central and Mobile Pre-Conditioned Air Equipment. It does not apply to aircraft mounted equipment
Selective catalytic reduction (SCR) of oxides of nitrogen (NOx) with gaseous ammonia is the leading technology used to meet on- and off-highway NOx emission standards across the world. In typical SCR systems, a low-pressure injector introduces a solution of urea and water (UWS) into hot exhaust gases leading to atomization and subsequent spray processes that finally lead to production of gaseous ammonia. Through their synergetic effect, the UWS injector and mixing enhancement devices (such as static mixers or baffles) help deliver a uniform mixture of ammonia and NOx to the SCR catalyst with minimal urea-derived solid deposits. To develop an efficient and robust aftertreatment system, it is essential to have experimental and simulation capabilities to assess the behavior of sprays under flow conditions representative of engine exhaust. The experimental part of the present work uses an optically accessible, cold- or hot-flow capable test section (called Insitu test section) that allows
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
This SAE Aerospace Standard (AS) covers one type of maximum-allowable-airspeed instrument which gives a continuous indication of both indicated airspeed and maximum allowable airspeed not exceeding 650 knots
This document describes recommended methods, associated equipment, and test setups to assist in understanding and conducting pressure drop tests on fuel system components. Background information and suggestions are provided to improve accuracy and repeatability of test results. Although written specifically for fuel system components, the methods, equipment, and suggestions presented herein apply equally to pressure drop tests conducted on any equipment utilizing incompressible fluids
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
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
In efforts to increase the accuracy and reliability of altimetry, speed measurement and other aspects of air data, a great deal of attention and money have been expended on new and refined pressure transducing and computing systems and on the standards by which they are calibrated. So much progress has been made in this that the limiting factor is, or may soon be, the sensing and transmitting in the aircraft of the pressures to be transduced. Until the appearance of References 1-13 and 18 there was little guidance available on the maintenance of pitot and static systems. This report presents what information is available, suggests limits, and lists the principal original papers on the subject
AIR1608 ESTIMATION OF TOTAL ERROR IN ALTIMETRY proposes a method of estimating overall error of altimetry in order to provide a basis for safe vertical separation of aircraft
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
NASA’s Langley Research Center has developed a new method for calibrating pitot-static air data systems used in aircraft. Pitot-static systems are pressure-based instruments that measure the aircraft’s airspeed. These systems must be calibrated in flight to minimize potential error. Current methods — including trailing cone, tower fly-by, and pacer airplane — are time- and cost-intensive, requiring extensive flight time per calibration. NASA’s method can reduce this calibration time by up to an order of magnitude, cutting a significant fraction of the cost. In addition, NASA’s calibration method enables near-real-time monitoring of error in airspeed measurements, which can be used to alert pilots when airspeed instruments are inaccurate or failing. Because of this feature, the technology also has applications in the health usage and monitoring (HUMS) industry. Flight test engineers can be trained to use this method proficiently in 12 days without costly specialized hardware
This document establishes the minimum requirements for ground based aircraft deicing/anti-icing methods and procedures 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 requirements 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 requirements 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 SAE Recommended Practice, limited to liquid coolant systems, establishes uniform vehicle heater test procedures. Both laboratory and complete vehicle tests are specified in this document. Required test equipment, facilities, and definitions are included
Nearly every military and commercial aircraft in the United States today uses pitot-static probes for accurate, repeatable airdata measurements. Recently, local angle-of-attack- and sideslip-sensing capabilities have been added to these probes to satisfy requirements for advanced aircraft with extended maneuvering envelopes. Probes made in advanced shapes to satisfy these requirements have been evaluated in wind-tunnel tests at angles of attack up to 90°, with favorable results. Flight tests of the Advanced L-probe Air Data Integration (ALADIN) program, directed toward evaluating the performances of these probes, were recently concluded at NASA Dryden Flight Research Center
A novel airdata system based on flush-mounted pressure sensors has been developed for the X-33 aerospace vehicle. Denoted the "X-33 flush airdata sensing" (FADS) system, it was designed to overcome limitations of pitot-static probes that were used previously, as explained below
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 Aerospace Standard (AS) specifies minimum performance requirements for primary pressure altimeter systems other than air data computers. This AS covers altimeter systems that measure and display altitude as a function of atmospheric pressure. The pressure transducer may be contained within the instrument display case or located remotely. Requirements for air data computers are specified in AS8002. Some requirements for nontransducing servoed altitude indicators are included in AS791. The instrument system specified herein does not include aircraft pressure lines. Unless otherwise specified, whenever the term "instrument" is used, it is to be understood to be the complete system of pressure transducer components, any auxiliary equipment, and display components. The test procedures specified herein apply specifically to analog type instruments. Digital instruments or automatic test instrumentation may require other test procedures. Such differing procedures shall be justified prior
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
In efforts to increase the accuracy and reliability of altimetry, speed measurement and other aspects of air data, a great deal of attention and money have been expended on new and refined pressure transducing and computing systems and on the standards by which they are calibrated. So much progress has been made in this that the limiting factor is, or may soon be, the sensing and transmitting in the aircraft of the pressures to be transduced. Until the appearance of References 1-13 and 18 there was little guidance available on the maintenance of pitot and static systems. This report presents what information is available, suggests limits, and lists the principal original papers on the subject
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 standard covers three (3) basic types of flight recorders as defined below: All requirements specified in sections 3, 4, 5, 6 & 7 of this standard shall be applicable to all recorder types unless otherwise noted
In efforts to increase the accuracy and reliability of altimetry, speed measurement and other aspects of air data, a great deal of attention and money have been expended on new and refined pressure transducing and computing systems and on the standards by which they are calibrated. So much progress has been made in this that the limiting factor is, or may soon be, the sensing and transmitting in the aircraft of the pressures to be transduced. Until the appearance of References 1-13 and 18 there was little guidance available on the maintenance of pitot and static systems. This report presents what information is available, suggests limits, and lists the principal original papers on the subject
This SAE Recommended Practice, limited to liquid coolant systems, establishes uniform vehicle heater test procedures. Both laboratory and complete vehicle tests are specified in this recommended practice. Required test equipment, facilities and definitions are included. NOTE: Defrosting and defogging procedures and requirements can be found in SAE J902b, J381, J382, and J953
The scope of this SAE Recommended Practice is sufficiently broad that it can encompass the full range of current heavy duty vehicles, vehicle modifications, and prototype configurations. The test procedure describes methods for examination of the vehicle’s flow field using surface pressures and flow visualization
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