Дисертації з теми "Helicopter flight operations"
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Lentz, Frederick Charles. "Integration of ASW helicopter operations and environment into NPSNET." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1995. http://handle.dtic.mil/100.2/ADA304302.
Повний текст джерела"September 1995." Thesis advisor(s): Michael J. Zyda, John S. Falby. Includes bibliographical references (p. 107). Also available online.
Ngo, Tri Dinh. "Constrained Control for Helicopter Shipboard Operations and Moored Ocean Current Turbine Flight Control." Diss., Virginia Tech, 2016. http://hdl.handle.net/10919/71685.
Повний текст джерелаPh. D.
Shafer, Daniel Manfred. "Active and Passive Flow Control over the Flight Deck of Small Naval Vessels." Thesis, Virginia Tech, 2005. http://hdl.handle.net/10919/32427.
Повний текст джерелаMaster of Science
Pereira, Figueira José Márcio. "The use of offline simulation tools to estimate ship-helicopter operating limitations." Thesis, Aix-Marseille, 2017. http://www.theses.fr/2017AIXM0511/document.
Повний текст джерелаHelicopter land-based limitations are not valid in the shipboard environment. There is no analytical or simulated approved methodology for evaluating shipboard helicopter compatibility issues and preparing for at-sea flight tests. In this context, the present work presents the development and analysis of an offline methodology to determine the Ship-Helicopter Operating Limitations, SHOLs, based on pilot model predictions. For this, pilot-in-the-loop simulation trials are performed at the engineering fixed-base simulation facility of ONERA, Salon de Provence. Based on these test results, an innovative methodology is proposed and validated to determine the safe pilot workload limitation, from the measurements of the helicopter control displacements. In addition, it is proposed and validated innovative modifications on a classical pilot model enabling to follow complex predefined desired trajectories and provide the same level of control activity of a real pilot. A set of objective criteria, corresponding to the safety margins, is established in addition to the subjective criteria, corresponding to the safe pilot workload limitations. An offline simulation routine, so-called SholSim, is coded to run all models and verify the acceptability of the flight conditions, according to the subjective and objective criteria. Therefore, the present work presents the first estimation, in the literature, of the SHOLs fully obtained from offline tools, based only on pilot model predictions. The proposed methodology is promising, confirmed by predicting coherent limits when compared to the ones defined by the pilot-in-the-loop simulation trials
DERE, Ahmet Murat. "Flight regime recognition analysis for the army UH-60A IMDS usage." Thesis, Monterey, California. Naval Postgraduate School, 2006. http://hdl.handle.net/10945/2510.
Повний текст джерелаUsage Monitoring requires accurate regime recognition. For each regime, there is a usage assigned for each component. For example, the damage accumulated at a component is higher if the aircraft is undergoing a high G maneuver than in level flight. The objective of this research is to establish regime recognition models using classification algorithms. The data used in the analysis are the parametric data collected by the onboard system and the actual data, consisting of the correct regime collected from the flight cards. This study uses Rpart (with a tree output) and C5.0 (with a ruleset output) to establish two different models. Before model fitting, the data was divided into smaller datasets that represent regime families by subsetting using important flight parameters. Nonnormal tolerance intervals are constructed on the uninteresting values; then these values in the interval are set to zero to be muted (e.g. excluded). These processes help reduce the effect of noise on classification. The final models had correct classification rates over 95%. The number of bad misclassifications were minimized (e.g. the number of bad misclassifications of a level flight regime as a hover regime was minimized), but the models were not as powerful in classifying the low-speed regimes as in classifying high-speed regimes.
Outstanding Thesis
Forrest, James Stephen. "Predicting ship-helicopter operating limits using time-accurate CFD ship airwakes and piloted flight simulation." Thesis, University of Liverpool, 2009. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.526869.
Повний текст джерелаJohnson, Kevin Lee. "Prediction of operational envelope maneuverability effects on rotorcraft design." Diss., Georgia Institute of Technology, 2013. http://hdl.handle.net/1853/47601.
Повний текст джерелаRevor, Mark S. "An analysis of the integrated mechanical diagnostics health and usage management system on rotor track and balance." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2004. http://library.nps.navy.mil/uhtbin/hyperion/04Jun%5FRevor.pdf.
Повний текст джерелаThesis advisor(s): Lyn R. Whitaker, Arnold H. Buss. Includes bibliographical references (p. 77-78). Also available online.
Unnikrishnan, Suraj. "Adaptive Envelope Protection Methods for Aircraft." Diss., Georgia Institute of Technology, 2006. http://hdl.handle.net/1853/11478.
Повний текст джерелаPraveen, B. "Study of the ship airwake-helodeck flow field for safe helo operations." Thesis, 2018. http://localhost:8080/xmlui/handle/12345678/7776.
Повний текст джерелаYang, Tzu-Chien, and 楊子健. "A Study on New Attack Helicopter with Unmanned Flight Vehicle System in Anti-landing Operations." Thesis, 2019. http://ndltd.ncl.edu.tw/handle/fy45zy.
Повний текст джерела崑山科技大學
資訊管理研究所
107
With the modernization of the Armed Forces in China, the CCP's technology is developing rapidly by the along of economic growth recently. Consequently, its weapons and equipments were evolving with each passing day. No matter from information, missiles, and space technology, it is far superior compared to the armed force. Especially, the CCP accelerated the missile's ability to project capability with the high precision after the Gulf War. The ability to anti-missile is an important part of high-tech for long-distance missile projection. In response to the military threats, this studt focuses on using the AH-64E attack helicopter combined with the UAS system to perform an anti-armor attack as follows: 1. How to preserve the combat power under the threat of enemy forces, missiles, air forces and other threats, by incorpotating AH-64E attack helicopter with unmanned aerial vehicle (UAV) system, to assist the commander recognize the whole battlefield. The solution makes it play an important role in defeating the enemy, which means first seeking the whole army and then defeating the enemy. 2. The army continuly gains the AH-64E attack helicopter and UH-60M universal. By incorporating helicopter with UAV information, communication advantages, and the AH-64E attack helicopter, it will expand the battlefield intelligence integration function, speed up the target timeliness and enhance the target strike capability, and make the land navigation operations more effective.
Sung, Le-Yeh, and 宋樂業. "Human Factors Analysis for Helicopter Flight Operation." Thesis, 2006. http://ndltd.ncl.edu.tw/handle/76695435579766537165.
Повний текст джерела國立成功大學
高階管理碩士在職專班
94
In the passed decade, the average accident rate is approximately 1.66 mishaps per million flight hours for the Republic of China (ROC) civil aircraft and it is 3.07 times of the World's average --- 0.54 mishaps per million flight hours. In addition, the average accident rate is 34.08 mishaps per 100,000 flight hours for the ROC rotor-wing aircraft while it is 8.74 for the USA rotor-wing aircraft. The ROC helicopter accident rate is almost 4 times of the USA accident rate. According to the data I mentioned above, the ROC flight safety is a concern when it is compared to the current world's flight safety level, especially the flight safety for helicopters. However, there are few exclusive researches for helicopter flight safety among the countless researches related to aviation/flight safety. As we know, flight safety is affected by many factors. The accident statistics tell us that the 70% flight accidents are caused by human factors. The purpose of this study is to determine the critical human factors that affect helicopter flight safety most and figure out a way to improve the flight safety level in our country. We include "Organization" among the SHEL model (Software, Hardware, Environment, and Liveware) to establish the HELLOS model which is emphasized on "liveware and liveware(s)" because we found that the human factors in accident were evolving from "individual" to "group". We hope the HELLOS could be more completed for analyzing the human factors. In this study, we received diverse data from government, civilian airlines, and militarizes and used quantitative methods for research. After factor screening and priority sorting, we draw a chart with quantitative scale called "Human Risk Factor for Helicopter Flight Safety", including 5 topical subjects and 17 factors. The priority order of topical subjects is: 1. Liveware and liveware. 2. Liveware and software. 3. Liveware and organization. 4. Liveware and environment. 5. Liveware and hardware.The 17 factors discussed in each topical subject are(Selections of first 10 item in 17): 1. Follow the Crew Resource Management (CRM) principles or not? 2. Flight safety cognition. 3. Environment or the vibration caused by aircraft. 4. The unhealthy equipment. 5. Pilot self-discipline. 6. Standard Operating Procedure (SOP) or regulations are feasible or not? 7. Familiar with the upcoming mission or not? 8. Training is valid or not? 9. Follow SOP exactly?10. Pilots' physiological functions. According to the affections and feasibilities of factors, we create the "Policy Schema" and divide those factors into the first priority group, priority planning group, flexible integration group, and long-term planning group. Policymakers refer to the distributions of those factors in Policy Schema and resources available for decision-making. A remarkable and effective flight safety improvement with minimum investment should be expected.
Su, Yinyi, and 蘇殷逸. "Numerical Investigation on Influence of Engine Exhaust on Flight Operation of Shipboard Helicopter." Thesis, 2011. http://ndltd.ncl.edu.tw/handle/42465699817330907929.
Повний текст джерела國防大學理工學院
造船及海洋工程碩士班
99
The exhausted gases from ships upper smoke are corrosive. They will erode and pollute the equipments on the deck, harm the people’s health on the ship deck, even threat the flight crew’s safety. So, predicting the plume trajectory is necessary and helpful. The factors influent the plume flow are numerous and complicated, such as wind velocity, exhausted gases velocity from the plume, the plume temperature, the plume height, the front structures, and so on, all of them will affect the gases flow. For preventing the gases create damage, we need to make design to change its path for decreasing the possibility to hurt the people and machine, the more important is to ensure the flight crew’s safety. This paper will use CFD(Computational Fluid Dynamics) to simulate the ship plume flow and helicopter’s motion, and will analysis the Perry Class vessel and the helicopter S70-C. The purpose is to discuss the influent from superstructures, the shape of the plume, the wind deflectors, and the helicopter’s motion. In the helicopters part, we will use the sliding mesh technique to simulate the flow when the helicopter is hovering, and establish the ship model to provide the ship design and development.
Kuo-MingChu and 朱國明. "Analysis of Digital to Analog Flight Instruments in Helicopter Cockpit Against Pilot’s Operation Margin." Thesis, 2013. http://ndltd.ncl.edu.tw/handle/73010238147679945232.
Повний текст джерела國立成功大學
航空太空工程學系專班
101
In the process of aviation evolution, the structure of airframe, composite materials and the power technology improve persistently. The primary goal of all these improvement was to speed up the aircraft, increase the flight altitude, extend travel distance, and expand the carrying capacity. Nevertheless, the complexity of aviation system has been influencing pilot's aircraft manipulation. Statistics showed, according to ICAO, that more than 70 percent of aircraft accidents directly or indirectly related to incorrect pilot manipulation. Therefore, the modern aviation system has introduced the concept of human factors engineering to interface of flight instruments cockpit and integrated them into the digital avionics system. This research probes the influence of digital avionics upon pilot's ability training. In the flight of pilot's training and achievement, both of the TH-67 helicopter simulator equipped with analogical flight instruments and CH-47SD full digital flight instruments cockpit are applied to sample and analyze pilot operation margin verity and emergency manipulation procedures. This research also deeply proves that digital avionics do improve pilot's flight manipulation and aviation security efficiency. 645 items of flight emergency procedures are exercised with 396 effective sampling adopted (including 216 of helicopter simulator and 180 of actual aircraft). Under deliberate analysis, the quantification data has verified that the digital avionics can provide pilots with a larger operation margin and shorten the judgment time under emergency situation. It is very obvious to see that the digital avionics can not only alleviate pilot's pressure but also enhance the aviation security.
Wei, Hwang Jyh, and 黃志偉. "A Study on the Safe Operating Envelopes of a Helicopter/Ship Landing Set by Flight Qualities." Thesis, 2006. http://ndltd.ncl.edu.tw/handle/59744187163557853388.
Повний текст джерела國防大學中正理工學院
兵器系統工程研究所
94
In this thesis, the investigation of onboard helicopter flight safe operating envelopes in different kinds of sea conditions set by flying qualities during landing are of particular interest. This thesis includes five key steps: Firstly, incorporating the six degree-of-freedom equations of motion and the steady-state airwake on the flight deck, the helicopter/ship recovery model is established. Second, we analyse the influence of ship speed and wave cycle to the ship motions in different kinds of sea conditions. Third, three kinds of controller are designed by flight quality to simulate the driving technologies and experiences of the three levels of pilot. The Quickness Criteria flight qualities in ADS-33 are introduced to determine the closed loop poles. Fourth, we define the theoretical flight safe operating envelope of onboard helicopter and the simulation processes to determine the theoretical flight safe operating envelope for helicopter landing on a ship. Fifth, the differences of the theoretical flight safe operating envelopes in different kinds of sea conditions and controllers are studied. Finally, we use of Matlab in Virtual reality Toolbox to simulate the scene when a helicopter lands on a ship. This thesis is expected to be helpful to the pilot training, flight safety and analysis of the margin of the helicopter/ship flight safe operating envelope.