Browse Topic: Stall warning indicators

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Formal Technique for Fault Detection and Identification of Control Intensive Application of Stall Warning System Using System Theoretic Process Analysis2024-26-04716/1/2024
Faults if not detected and processed will create catastrophe in closed loop system for safety critical applications in automotive, space, medical, nuclear, and aerospace domains. In aerospace applications such as stall warning and protection/prevention system (SWPS), algorithms detect stall condition and provide protection by deploying the elevator stick pusher. Failure to detect and prevent stall leads to loss of lives and aircraft. Traditional Functional Hazard and Fault Tree analyses are inadequate to capture all failures due to the complex hardware-software interactions for stall warning and protection system. Hence, an improved methodology for failure detection and identification is proposed. This paper discusses a hybrid formal method and model-based technique using System Theoretic Process Analysis (STPA) to identify and diagnose faults and provide monitors to process the identified faults to ensure robust design of the indigenous stall warning and protection system (SWPS). The technique is implemented for the SWPS system to ensure the detection of faults due to electric, sensor and computational integrity. Once a fault is detected, a graceful degradation of system functionality is ensured, and appropriate caution/warning annunciations are provided to alert the crew. This has been analyzed and demonstrated on the simulated platform. Proposed Methodology uses the Concept of Operations and STPA to derive the control logic model for monitors for fault detection and identification. These monitors analyze data from angle of attack sensors, Air data computational units and Attitude heading reference system for developing a robust logic for SWPS to minimize both false positives and false negatives. The efficacy of the proposed hybrid technique has been demonstrated on the real time flight simulator with aircraft flight data
Kale, Alexander, Madhuranath, Ganesh, Shanmugham, Viswanathan, Nanda, Manju, Singh, Giresh, Durak, Umut
STALL WARNING INSTRUMENTAS403A (Current)8/4/2022
A-4ADWG Air Data Subcommittee
Minimum Performance Standard Stall Warning EquipmentAS8014A (Current)12/22/2020
This Aerospace Standard covers two basic Stall Warning Systems, one measures air flow and pressure distribution on the airfoil and the other measures the angle of airflow with respect to an arbitrary reference line. Each type of system includes, as a minimum, a sensor and the means for activating a device which warns the pilot of an impending stall.
A-4 Aircraft Instruments Committee
AIRBORNE WINDSHEAR SYSTEMSARP4102/11 (Historical)7/1/1988
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.
S-7 Flight Deck Handling Qualities Stds for Trans Aircraft
Statistical Analysis of General Aviation Stall Spin Accidents7604802/1/1976
This paper represents the results of a computer study of General Aviation accidents, particularly stall and spin accidents. In an introductory review, five transportation modes are compared on the basis of deaths per 100,000,000 passenger-miles. Of these, General Aviation has the highest accident rate, and domestic airlines the lowest. Descriptions of four “stall-related” accident types (stall, spin, spiral and mush) are given. A summary for these four accident types over the years 1965 through 1973 is given for both twin- and single-engine aircraft. The patterns are found to be similar. Stall/spin accident patterns are reviewed for a group of 31 single-engine aircraft (1965-1973) by: kind of flying, phase of flight, turning flight, airport proximity, weather, daylight, pilot experience and age, stall warning indicator, and cause of accident. Individual results are presented for the 31 aircraft by make and model. A Chi-Square statistical test shows that some of these aircraft have significantly higher (or lower) stall/spin accident rates than the group mean. Several recommendations are offered for consideration in improving General Aviation safety.
Silver, Brent W.
A Systematic Study Of Helicopter Rotor Stall Using Model RotorsVFS-F30-0055/7/1974
A wind tunnel test was conducted to systematically determine the effects of twist, camber, taper ratio, number of blades, and torsional frequency on model helicopter rotor stall characteristics. Model rotor performance, blade response, and boundary layer separation data were acquired at low Reynolds and Mach numbers to determine the occurrence and extent of blade stall. Boundary layer information was obtained by means of hot-film gages installed over the outer 25-percent span on the suction surface of two blade designs. The data obtained indicated consistently the azimuthal, chordwise, and radial location of stall onset and recovery and the laminar/turbulent transition of the boundary layer. The rotor lift at the stall threshold, indicated by hot-film measurements, was generally coincident with a change in rate of lift growth, vibratory flapping, and vibratory edgewise stress with increasing rotor shaft angle. Based on the average of these stall indicators, the effects of the various design parameters on stall were determined for advance ratios of 0.15, 0.30 and 0.45. Camber and taper provided the greatest improvement in delaying stall and stalled rotor performance. Lowering the torsional frequency tended to delay the onset of stall flutter.
Landgrebe, Anton J., Bellinger, E. Dean
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