Log in

Relevant bibliographies by topics / Aircraft guiding

Contents

Journal articles
Dissertations / Theses
Conference papers

Academic literature on the topic 'Aircraft guiding'

Author: Grafiati

Published: 4 June 2021

Last updated: 1 February 2022

Create a spot-on reference in APA, MLA, Chicago, Harvard, and other styles

Select a source type:

Consult the lists of relevant articles, books, theses, conference reports, and other scholarly sources on the topic 'Aircraft guiding.'

Next to every source in the list of references, there is an 'Add to bibliography' button. Press on it, and we will generate automatically the bibliographic reference to the chosen work in the citation style you need: APA, MLA, Harvard, Chicago, Vancouver, etc.

You can also download the full text of the academic publication as pdf and read online its abstract whenever available in the metadata.

Journal articles on the topic "Aircraft guiding"

1

Yang, Qin Yu, Jin Bo Yao, Yue Ming Yang, and Xue Wei Liu. "In the Wind Tunnel Simulation Defroster Control Study." Applied Mechanics and Materials 380-384 (August 2013): 191–94. http://dx.doi.org/10.4028/www.scientific.net/amm.380-384.191.

Full text

Abstract:

Aircraft in flight, such as supercooled water droplets encountered icing conditions suitable for the external environment, the relevant parts of the body will freeze, making the aircraft's aerodynamic performance deterioration, severe endanger flight safety, in addition, the aircraft parked in the open winter months , there will be icing, you need to clean up before takeoff. We should grasp the mechanism of aircraft icing, environmental factors and easy to freeze parts of the body. This paper presents a simulation using the wind tunnel icing device icing wind tunnel simulations can reproduce the real situation of aircraft icing, for guiding practice and got good results.

APA, Harvard, Vancouver, ISO, and other styles

2

Yao, Jin Bo, Yue Ming Yang, Qin Yu Yang, Xiu Juan Liu, and Dun Jin. "Application of LED Light Source in the Flow Imaging." Applied Mechanics and Materials 380-384 (August 2013): 219–22. http://dx.doi.org/10.4028/www.scientific.net/amm.380-384.219.

Full text

Abstract:

Aircraft in flight, such as supercooled water droplets encountered icing conditions suitable for the external environment, the relevant parts of the body will freeze, making the aircraft's aerodynamic performance deterioration, severe endanger flight safety, in addition, the aircraft parked in the open winter months , there will be icing, you need to clean up before takeoff. We should grasp the mechanism of aircraft icing, environmental factors and easy to freeze parts of the body. This paper presents a simulation using the wind tunnel icing device icing wind tunnel simulations can reproduce the real situation of aircraft icing, for guiding practice and got good results.

APA, Harvard, Vancouver, ISO, and other styles

3

Zhao, Xin Can, and Zhen Hua Wen. "Information Organization of Augmented Reality Maintenance Guiding System." Applied Mechanics and Materials 197 (September 2012): 523–28. http://dx.doi.org/10.4028/www.scientific.net/amm.197.523.

Full text

Abstract:

The information organization and expression is a key issue for the Augmented Reality Maintenance Guiding System（ARMGS）. In this paper, we firstly build up the relationship between the aircraft maintenance manual, EBOM figure and virtual prototype data , then construct a prototype of Interactive Electronic Technical Manual (IETM). The system can convert the aircraft virtual prototype data to the required information for augmented reality maintenance guiding system, based on the information, the prototype can be rapidly and lifelikely displayed. The system proposed in this paper significantly improves the quality and effectiveness of modeling.

APA, Harvard, Vancouver, ISO, and other styles

4

Zikmund, Pavel, Lukáš Dubnický, Michaela Horpatzká, Miroslav Macík, and Ivo Jebáček. "Flight Test of Pilot-Aircraft Haptic Feedback System." MATEC Web of Conferences 304 (2019): 06005. http://dx.doi.org/10.1051/matecconf/201930406005.

Full text

Abstract:

This research is focused on an innovative improvement of pilot-aircraft interaction and is targeted on small aircraft. Haptic feedback is performed by actuators mounted on an aircraft's controls. The purpose of the actuators on a control stick and pedals is stall warning and a pilot guiding to safe and economical flight regimes. The feedback system mediates airflow data as angles of attack and sideslip. The paper brings results of a flight test of the proposed system. Qualitative evaluation of the haptic feedback inflight is presented. Benefits of the system are presented on a sideslip during turning. Some recommendations for the haptic pilot-aircraft interaction are stated within the discussion of the flight test results.

APA, Harvard, Vancouver, ISO, and other styles

5

Harinarayana, Kota. "Developing light combat aircraft: foresight as the guiding principle." International Journal of Foresight and Innovation Policy 1, no. 3/4 (2004): 325. http://dx.doi.org/10.1504/ijfip.2004.004967.

Full text

APA, Harvard, Vancouver, ISO, and other styles

6

Botkin, Nikolai D., Alexey E. Golubev, and Varvara L. Turova. "Aircraft Guiding in Windshear through Differential Game-Based Overload Control." IFAC-PapersOnLine 52, no. 16 (2019): 706–11. http://dx.doi.org/10.1016/j.ifacol.2019.12.045.

Full text

APA, Harvard, Vancouver, ISO, and other styles

7

Garcia, Gonzalo, and Shahriar Keshmiri. "Adaptive and Resilient Flight Control System for a Small Unmanned Aerial System." International Journal of Aerospace Engineering 2013 (2013): 1–25. http://dx.doi.org/10.1155/2013/289357.

Full text

Abstract:

The main purpose of this paper is to develop an onboard adaptive and robust flight control system that improves control, stability, and survivability of a small unmanned aerial system in off-nominal or out-of-envelope conditions. The aerodynamics of aircraft associated with hazardous and adverse onboard conditions is inherently nonlinear and unsteady. The presented flight control system improves functionalities required to adapt the flight control in the presence of aircraft model uncertainties. The fault tolerant inner loop is enhanced by an adaptive real-time artificial neural network parameter identification to monitor important changes in the aircraft’s dynamics due to nonlinear and unsteady aerodynamics. The real-time artificial neural network parameter identification is done using the sliding mode learning concept and a modified version of the self-adaptive Levenberg algorithm. Numerically estimated stability and control derivatives are obtained by delta-based methods. New nonlinear guidance logic, stable in Lyapunov sense, is developed to guide the aircraft. The designed flight control system has better performance compared to a commercial off-the-shelf autopilot system in guiding and controlling an unmanned air system during a trajectory following.

APA, Harvard, Vancouver, ISO, and other styles

8

Lu, Hua-An, and Tsung-Yi Chou. "Design Factors of Guiding Aircraft Through Continuous Descent Operations: Pilot and Controller Perspectives." International Journal of Aerospace Psychology 29, no. 1-2 (April 3, 2019): 1–16. http://dx.doi.org/10.1080/24721840.2019.1596743.

Full text

APA, Harvard, Vancouver, ISO, and other styles

9

Wu, Chunhui, and Stephane Redonnet. "Prediction of Aircraft Noise Impact with Application to Hong Kong International Airport." Aerospace 8, no. 9 (September 15, 2021): 264. http://dx.doi.org/10.3390/aerospace8090264.

Full text

Abstract:

As part of a collective research effort towards greener aviation, the present study focuses on the noise impact of aircraft operations around major airports. To this end, an aircraft noise prediction platform is developed, which relies on state-of-the-art functionalities as well as more specific, innovative features. Originally built upon the Aircraft Noise and Performance (ANP) database and its Noise–Power–Distance (NPD) table, the method is further refined to alleviate most of their inherent limitations (e.g., standardized and simplified aircraft noise scenarios). The resulting aircraft noise prediction platform is validated against benchmark cases of increasing complexity, being then applied to real-life situations involving actual aircraft operations around Hong Kong International Airport (HKIA). Specific comparative analyses are conducted, which allow highlighting the variability of the noise impact by aircraft, depending on their type (A330, B777) and/or operational conditions (power settings, meteorological conditions, routes, banks, etc.). The study delivers insightful outcomes, whether phenomenological (aircraft noise impact) or methodological (aircraft noise prediction). As a by-product, it illustrates how noise prediction methods/platforms such as the present one may help in guiding the further expansion of airport operations and/or infrastructures (as is currently the case with HKIA).

APA, Harvard, Vancouver, ISO, and other styles

10

Zu, Wenqiang, Hongyu Yang, Renyu Liu, and Yulong Ji. "A Multi-Dimensional Goal Aircraft Guidance Approach Based on Reinforcement Learning with a Reward Shaping Algorithm." Sensors 21, no. 16 (August 21, 2021): 5643. http://dx.doi.org/10.3390/s21165643.

Full text

Abstract:

Guiding an aircraft to 4D waypoints at a certain heading is a multi-dimensional goal aircraft guidance problem. [d=Zu]In order to improve the performance and solve this problem, this paper proposes a multi-layer RL approach.To enhance the performance, in the present study, a multi-layer RL approach to solve the multi-dimensional goal aircraft guidance problem is proposed. The approach [d=Zu]enablesassists the autopilot in an ATC simulator to guide an aircraft to 4D waypoints at certain latitude, longitude, altitude, heading, and arrival time, respectively. To be specific, a multi-layer RL [d=Zu]approach is proposedmethod to simplify the neural network structure and reduce the state dimensions. A shaped reward function that involves the potential function and Dubins path method is applied. [d=Zu]Experimental and simulation results show that the proposed approachExperiments are conducted and the simulation results reveal that the proposed method can significantly improve the convergence efficiency and trajectory performance. [d=Zu]FurthermoreFurther, the results indicate possible application prospects in team aircraft guidance tasks, since the aircraft can directly approach a goal without waiting in a specific pattern, thereby overcoming the problem of current ATC simulators.

APA, Harvard, Vancouver, ISO, and other styles

More sources

Dissertations / Theses on the topic "Aircraft guiding"

1

Burke, D. M. "The study of errors in synchros and resolvers using numerical methods." Thesis, University of Newcastle Upon Tyne, 1991. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.239741.

Full text

APA, Harvard, Vancouver, ISO, and other styles

2

Lemay, David. "Commande multisystème hiérarchisée pour le pilotage d'un avion autonome au sol." Thesis, Orléans, 2011. http://www.theses.fr/2011ORLE2054.

Full text

Abstract:

Pour répondre à l’augmentation du trafic aérien mondial et à l’amélioration de la sécurité sur les plateformes aéroportuaires, le secteur aéronautique développe de nouveaux systèmes permettant de tendre vers l’autonomie complète de l’avion pendant les phases de roulage au sol. Le thème de ce travail de thèse concerne l’automatisation du pilotage de l’avion au sol et le développement d’une architecture de commande multivariable permettant de superviser l’ensemble des systèmes impliqués dans ce mode de déplacement : les systèmes de motorisation et de freinage des roues principales et le système d’orientation du train avant. Après une modélisation détaillée de la dynamique du système et une analyse des problématiques induites par ses non-linéarités, une architecture de commande globale est proposée. L’asservissement de la dynamique angulaire des roues, pendant les phases d’accélération et de freinage, est assuré par une loi de commande linéaire robuste aux incertitudes, synthétisée à l’aide de la technique Q.F.T. Le pilotage de la dynamique latérale du véhicule est réalisé au moyen d’un correcteur hybride feedforward-feedback. Une commande modale au premier ordre est alors mise en oeuvre afin de synthétiser un régulateur non-linéaire par planification de gains (gain-scheduling). L’ensemble des boucles d’asservissement de l’architecture est finalement validé en réalisant un suivi automatique de trajectoire à l’aide d’une commande géométrique nommée follow the carrot. Les simulations représentatives de l’utilisation réelle de l’avion démontrent des performances satisfaisantes et permettent de valider l’ensemble des solutions proposées
In the context of worldwide air traffic growth and airport security improvement, the main aeronautics actors are currently investigating new systems, strived for autonomously piloting the aircraft while taxiing ground-borne. The present thesis deals with aircraft taxiing control and the design of a multivariable control architecture aimed at supervising all the ground acting systems: driving and braking systems of main wheels and the nose landing gear steering system. A global control architecture is introduced after a detailed modelling of the system dynamics and an analysis of the issues induced by the nonlinearities. A linear Q.F.T controller is synthesised to ensure robust control against uncertainties of the wheel angular dynamics, in both driving and braking operations. The vehicle lateral dynamics is controlled by means of a feedforward-feedback hybrid controller. The latter includes a nonlinear gain-scheduled controller designed by a modal approach. All the architecture control loops are finally validated in a high level path following control, achieved with the “follow the carrot” geometric method. A set of representative simulations show the overall good performances and validate the whole proposed solution

APA, Harvard, Vancouver, ISO, and other styles

Conference papers on the topic "Aircraft guiding"

1

Santos, Milton Cesar Paes, Mario Sarcinelli-Filho, Alexandre Santos Brandao, and Ricardo Carelli. "A Controller Based on PVTOL Control Signals for Guiding a Quadrotor in 3D Navigation Tasks." In 2018 International Conference on Unmanned Aircraft Systems (ICUAS). IEEE, 2018. http://dx.doi.org/10.1109/icuas.2018.8453371.

Full text

APA, Harvard, Vancouver, ISO, and other styles

2

Davis, Ian L., and Mel Siegel. "Vision algorithms for guiding the automated nondestructive inspector of aging aircraft skins." In SPIE's 1993 International Symposium on Optics, Imaging, and Instrumentation, edited by Michael T. Valley, Nancy K. Del Grande, and Albert S. Kobayashi. SPIE, 1993. http://dx.doi.org/10.1117/12.163839.

Full text

APA, Harvard, Vancouver, ISO, and other styles

3

Liou, Meng-Sing, and Byung Joon Lee. "Minimizing Inlet Distortion for Hybrid Wing Body Aircraft." In ASME Turbo Expo 2010: Power for Land, Sea, and Air. ASMEDC, 2010. http://dx.doi.org/10.1115/gt2010-22378.

Full text

Abstract:

A study of boundary-layer-ingesting flow in an upper-mounted offset inlet in NASA’s hybrid wing body transport concept for achieving environmental and performance requirements has been carried out. The study aims specifically at minimizing flow distortion stemming from the ingested low-momentum fluid to the level acceptable to the operation of fan blades. In this paper, we will focus on using a discrete adjoint method to arrive at an optimized wall geometry, which is parametrically represented by design variables, for transonic turbulent flows described by 3D Navier-Stokes equations supplemented with κ–ω–SST turbulence model. Of special interest herein is the flow physics resulting from optimization, revealing the intricate connections to the remarkable reduction in flow distortion and total pressure losses at the engine face. It is discovered that the secondary counter-rotating vortex pair commonly seen in an S-inlet is eliminated by energizing both core and boundary-layer fluids through the change of wall shape by a series of peaks and valleys, whose magnitudes and wave forms being functions of locations and unknown a priori are determined by the discrete adjoint method. Moreover, the optimal shape still holds similar level of superior performance at off-design conditions. The result may suggest a possible paradigm shift in flow control concept, away from disruptive penalty-ridden devices, by properly conditioning and guiding the flow.

APA, Harvard, Vancouver, ISO, and other styles

4

Lee, Zoe, Rumit Kumar, Reza Radmanesh, Manish Kumar, and Kelly Cohen. "Application of Fuzzy Logic for Developing Sense and Avoid Techniques for UAV Flight Operations in National Airspace." In ASME 2020 Dynamic Systems and Control Conference. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/dscc2020-3268.

Full text

Abstract:

Abstract In this work, a Fuzzy Inference System (FIS) is proposed to develop a sense and avoid technique for conflict-free Unmanned Aerial Vehicle (UAV) flight operations in the national airspace. The proposed method is implemented alongside the flight control software guiding the UAV towards a predefined goal. The fuzzy system makes decisions for sense and avoid with respect to the state of other intruder aircraft in the airspace. The fuzzy rules are selected under consideration of the heading and position data of the intruder aircraft obtained using ADS-B sensor relative to the controlled UAV. The avoidance controller is implemented alongside a traditional PID-based flight controller to test the effectiveness of the sense-and-avoid technique. The PID controller drives the controlled UAV towards the goal and the fuzzy controller is for conflict avoidance based on an event trigger logic if the controlled UAV is in the intrusion zone of another aircraft. The integration of the dynamic model of the controlled UAV and fuzzy inference system is described. The numerical simulations are shown to evaluate the performance of the proposed method in the presence of moving as well as stationary intruder aircraft.

APA, Harvard, Vancouver, ISO, and other styles

5

Wang, Lei, Zong-quan Deng, Hao-di Wang, and Hong-hao Yue. "Analysis of Hybrid Programming Simulation Based on the Variable Stiffness Ring With Expanding Loop SMA Actuator." In ASME 2017 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/imece2017-71246.

Full text

Abstract:

In the development of space craft design index, the requirements of hypersonic space craft control accuracy has been increasingly rigorous. Thin-walled structure is often employed in hypersonic craft to reduce the weight of the load and to save the room. During the flight of the craft, temperature field is produced along the surface and the dynamic properties of the craft structure are obviously changed. The decreasing elastic modulus of the structure material and the appearance of thermal stress lead to the decrease of integral rigidity and stability of the structure, then the thermal flutter appears and control difficulties increase. Shape Memory Alloy (SMA) has the advantages of the considerable driving force in the compact volume and the simple driving method. By the combination of actuator structure design and stiffness control, the smart structure is able to make active control to the thermal stiffness variation. In this paper, the apex high-temperature area is equivalent to a ring structure. Finite difference method is employed firstly to transform the governing partial differential equation into discrete finite difference equations. Then the elastic modulus change, thermal stress and tension along the circumference are considered comprehensively to propose the calculation formulas of equivalent young’s modulus. The discrete dynamic matrix model is obtained containing the control terms of SMA. To solve the big-matrix calculation and multiple iterated large data problem, hybrid program is developed with C++ and MATLAB. Finite element software is employed to make optimization analysis to design an expanding loop actuator containing SMA as driving source, variable thickness loops of spring steel as expanding units, and universal-ball pre-loading units. On the basis of that, the thermal stiffness variation active control system with smart structure is developed based on expanding loop SMA actuator. After the analysis of examples, the variation law of the needed SMA driving force is obtained. The distribution position and quantity of the driving source is optimized. This research provides reference for the Theoretical Analysis and Simulation of structure stiffness active control and adaptive control of the aircraft employing smart material. The research results have guiding significance for the smart structure design of hypersonic aircraft in the future.

APA, Harvard, Vancouver, ISO, and other styles

6

Hurst, Adam M., and Joe VanDeWeert. "An Experimental and Theoretical Investigation of Wave Propagation in Teflon and Nylon Tubing With Methods to Prevent Aliasing in Pressure Scanners." In ASME Turbo Expo 2013: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/gt2013-96024.

Full text

Abstract:

Accurate static and dynamic pressure measurements provide the feedback needed to advance gas turbine efficiency and reliability as well as improve aircraft design and flight control. During turbine testing and aircraft flight testing, flush mounting pressure transducers at the desired pressure measurement location is not always feasible and recess mounting with connective tubing is often used as an alternative. Resonances in the connective tubing can result in aliasing within pressure scanners even within a narrow bandwidth and especially when higher frequency content DC to ∼125Hz is desired. We present experimental results that investigate tube resonances and attenuation in 1.35mm inner diameter (ID) (used on 0.063in tubulations) and 2.69mm ID (used on 0.125in tubulations) Teflon and Nylon tubing at various lengths. We utilize a novel dynamic pressure generator, capable of creating large changes in air pressure (<1psi to 10psi, <6.8kPa to 68.9kPa), to determine the frequency response of such tubing from ∼1Hz to 2,800Hz. We further compare these experimental results to established analytical models for propagation of pressure disturbances in narrow tubes. While significant theoretical and experimental work relating to the frequency response of connective tubing or transmission lines has been published, there is limited literature presenting experimental frequency response data with air as the media in elastic tubing. In addition, little progress has been made in addressing the issue of tubing-related aliasing within pressure scanners, as the low sampling rate in scanners often makes post-processing antialiasing filters ineffective. The experimental results and analytical models presented herein can be used as a guideline to prevent aliasing and signal distortion by guiding the proper design of pressure transmission systems, resulting in accurate static and dynamic pressure measurements with pressure scanners. The data presented here should serve as a reference to instrumentation engineers so that they can make higher frequency measurements (up to ∼125Hz, currently) and are able to quantify the expected pressure transmission line (tube) attenuation and know if aliasing will be a concern. This information will give engineers greater measurement capability when using pressure scanners to make static and dynamic pressure measurements.

APA, Harvard, Vancouver, ISO, and other styles

We offer discounts on all premium plans for authors whose works are included in thematic literature selections. Contact us to get a unique promo code!