Landing Approach Of Aircraft Research Articles

Noise pollution and violent crime☆

This paper reveals how exposure to noise pollution increases violent crime. To identify the causal effect of noise pollution, I use daily variation in aircraft landing approaches to instrument noise levels. Increasing background noise by 4.1 decibels causes a 6.6% increase in the violent crime rate. The additional crimes mostly consist of physical assaults on men. The results imply a substantial societal burden from noise pollution beyond health impacts.

Algorithm for evaluation the navigation complex of a carrier-based aircraft

The features of an aircraft landing approach on a moving aircraft carrier are studied. The main measuring systems used in landing approach for a carrier-based aircraft are inertial and satellite navigation systems. Joint signals processing in the navigation system is carried out by using an adaptive Kalman filter that can operate in the absence of a priori information about the statistical characteristics of the input noise. Kalman adaptive filter is based on using the properties of the updated sequence. The simulation results according to the semi-natural experiment showed its high efficiency.

HF DBD plasma actuators for reduction of cylinder noise in flow

Surface high frequency dielectric barrier discharge (HF DBD) was used to reduce flow-induced noise, radiated by circular cylinder in cross flow. Effect of HF DBD actuators is studied for flow velocity up to 80 m s−1 (Reynolds numbers up to 2.18 · 105), corresponding to the typical aircraft landing approach speed. Noise measurements were performed by microphone array in anechoic chamber; averaged flow parameters were studied by particle image velocimetry (PIV). Actuator was powered by high-frequency voltage in hundreds kHz range in steady or modulated mode with the modulation frequency of 0.3–20 kHz (Strouhal number St of 0.4 to 20). It is demonstrated that upstream directed plasma actuators are able to reduce the vortex noise of a cylinder by 10 dB. Noise reduction is accompanied by significant reorganization of the wake behind a cylinder, decreasing both wake width and turbulence level. The physical mechanism related to broadband noise control by HF DBD actuator is also discussed.

Evaluation of a Peripherally-Located Instrument Landing Display with High-Order Control of a Non-Linear Approach and Landing

We compared the precision of simulated-fixed wing aircraft landing approaches with two different head-up display (HUD) formats: a) the MIL-STD-1787B Instrument Landing System and b) a virtual peripherally-located optical flow ILS HUD. Within each display condition we compared a three second quickened display to a real time non-quickened display. Non-pilot participants used simplified controls to guide a landing simulation under night conditions with extremely poor visibility using Instrument Flight Rules (IFR). Participants followed a non-linear flight and approach path under the two display and quickening conditions. While quickening was found to have no significant effect, the peripheral optical flow ILS afforded greater overall precision in flight path control. The findings suggest an increased ability to extract rate-of-change information from the peripheral optical flow ILS affording improved spatial orientation.

Simulation of Accurate Navigation Technology for Aircraft Landing Approach

The purpose of this paper is to find a solid application and improve the integrated navigation system of aircraft independent landing. The main researches are focused on the issue how to improve the accuracy and reliability of the integrated navigation system, by means of the detailed analyzing about information fusion, and investigating accurate navigation technology for independent landing approach of aircraft. Next, the integrated navigation system models SINS/DGPS/TAN/ILS based on Federated filter are established, and the accurate navigation algorithm of landing is also researched. At the end, the paper gives its simulation results for independent lading approach, which show this algorithm is able to greatly improve the accuracy of speed and location information for aircraft accurate landing.

A Peripherally-Located Virtual Instrument Landing Display Affords More Precise Control of Approach Path during Simulated Landings than Traditional Instrument Landing Displays

We compared the precision of simulated fixed-wing aircraft landing approaches with three different head-up display (HUD) formats: a) MIL-STD-1787B Cruise Mode, b) MIL-STD-1787B Instrument Landing System (ILS) Mode, and c) a virtual ILS HUD presented to the visual periphery. Non-pilot participants used simplified controls to guide a landing simulation under both day and night visual meteorological conditions. Experiment 1 confirmed that testing non-pilots with our experimental setting could induce the black-hole illusion, in which the approach is lower than appropriate at night. Experiment 2 compared landing performance aided by the three HUD formats under the same visual conditions. We found that both ILS displays improved approach path precision as compared to the MIL-STD Cruise Mode, and that the peripherally-located virtual ILS HUD reliably afforded the greatest precision. These results suggest that ILS approaches may be better supported by presenting a virtual ILS display to the visual periphery.

Tunnel display for four-dimensional fixed-wing aircraft approaches

The present evaluation of a computer-generated perspective tunnel display for four-dimensional fixed wing aircraft landing approaches gives attention to the development and performance assessment of superimposed predictor symbology. Simulator tests indicate that a complex perspective vehicle symbol yields a decrease in bank angle activity, by comparison to a flat predictor cross, while yielding larger lateral and vertical deviations in most cases. The perspective vehicle symbol motions are successful in forward velocity control without affecting path-following performance. The perspective vehicle symbol's advantage over the flat predictor cross is nevertheless marginal. While the tunnel display used yields satisfactory response in the lateral control axis, the vertical axis lacks sensitivity to vertical path angle variations.

Evaluation of the Navigation performance of Shipboa VTOL Landing Guidance Systems

The objective of this study was to explore the performance of a VTOL aircraft landing approach navigation system that receives data (1) from either a microwave scanning beam (MSB) or a radar-transponder (R-T) landing guidance system, and (2) information data-linked from an aviation facility ship. State-of-the-art low-cost-aided inertial techniques and variable gain filters were used in the assumed navigation system. Compensation for ship motion was accomplished by a landing pad deviation vector concept that is a measure of the landing pad's deviation from its calm sea location. The results show that the landing guidance concepts were successful in meeting all of the current Navy navigation error specifications, provided that vector magnitude of the allowable error, rather than the error in each axis, is a permissible interpretation of acceptable performance. The success of these concepts, however, is strongly dependent on the distance measuring equipment bias. In addition, the 'best possible' closed-loop tracking performance achievable with the assumed point-mass VTOL aircraft guidance concept is demonstrated.

簡単化された航空機モデルによる最短時間と最小騒音着陸進入軌道

Optimal control theory is used to determine thrust and glide path angle programs for minimum time or minimum noise landing approach of aircraft modeled by an approximated point-mass dynamics. Necessary conditions for optimal programs are derived and numerical results are presented for a small jet airplane. Significant noise abatement and savings in time are obtained compared with reference thrust and path angle programs. The minimum time solution indicates; 1) thrust is a dominant control, and glide path angle γ has little influence on the performance index; 2) Optimal path mainly consists of a constant velocity descending path, which is a singular solution, and a decelerating path with γmax. Optimal thrust switches from its maximum to its minimum on the latter path. The minimum noise solution indicates; 1) optimal thrust has neither its maximum nor its minimum, and varies continuously so as to achieve a smooth EPN level curve; 2) optimal path mainly consists of a decelerating horizontal path and a decending path with γmax. These results may be regarded as a theoretical base for a two-segment approach for noise abatement and time savings.

Data Compression in Recursive Estimation with Applications to Navigation Systems

The goal of data compression or preprocessing is to reduce computational requirements in a Kalman filter while retaining adequate estimation accuracy. A technique which averages batches of data is considered here. Guidelines are given for averaging, such as, how often to sample the data, when to average, and how many data points to average. The averaging technique is applied to aircraft navigation using two DMEs and either air data or inertial data. The results demonstrate that significant computation time reductions are possible with some covariance degradation. VOR/DME flight data of aircraft landing approaches were used to verify the analysis and show agreement with the analytical predictions.

Fully automatic aircraft-landing approach

Fully automatic aircraft-landing approach

Fully automatic aircraft landing approach

Fully automatic aircraft landing approach