Gotowe bibliografie tematyczne / Aircraft protection

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Gotowa bibliografia na temat „Aircraft protection”

Autor: Grafiati

Data publikacji: 6 września 2023

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Artykuły w czasopismach na temat "Aircraft protection"

Taro, Sultan Ahmed, i Muhammed Abbas Hamoodi. "Criminal Protection of Aircraft". International Journal of Law and Politics Studies 5, nr 3 (3.06.2023): 153–62. http://dx.doi.org/10.32996/ijlps.2023.5.3.8.

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Human transportation, including travel, tourism, trade and transportation of goods through airspace has become one of the necessities and features of this era. Because of the technological development that the world has witnessed and its reflection on transportation, especially air transportation which is distinguished from other means in terms of the merit of speed, comfort and costs, the criminal protection of civil aviation, in addition to the national protection law, has organized it through international conventions such as Chicago Convention, Geneva Convention on the High Seas, Tokyo and Montreal Conventions. However, national and international protection did not prevent crimes against aircraft, rather, due to these developments, this crime has taken many other new forms. After the September 11 attack, even the aircraft was being used to attack civilians and governmental organs. Although substantive and procedural rules in international and national legislations protect aircraft, new forms of this crime which have emerged shall be addressed and complementary jurisdiction shall be adopted not to leave any legal gaps in criminal protection for aircraft.

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Babashov, V. G., i N. M. Varrik. "Trends in the development of flexible thermal protection systems for modern aircraft". Perspektivnye Materialy, nr 11 (2020): 10–21. http://dx.doi.org/10.30791/1028-978x-2020-6-10-21.

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The emergence of new types of space and aviation technology necessitates the development of new types of thermal protection systems capable of operating at high temperature and long operating times. There are several types of thermal protection systems for different operating conditions: active thermal protection systems using forced supply of coolant to the protected surface, passive thermal protection systems using materials with low thermal conductivity without additional heat removal, high-temperature systems, which are simultaneously elements of the bearing structure and provide thermal protection, ablation materials. Heat protection systems in the form of rigid tiles and flexible panels, felt and mats are most common kind of heat protecting systems. This article examines the trends of development of flexible reusable heat protection systems intended for passive protection of aircraft structural structures from overheating.

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尹, 扬. "Transport Aircraft Self-Protection Technology". Dynamical Systems and Control 07, nr 03 (2018): 232–38. http://dx.doi.org/10.12677/dsc.2018.73025.

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Almeraya-Calderón, Facundo, i Jose Chacon-Nava. "Corrosion and Protection in Aeronautical Alloys". Metals 13, nr 6 (6.06.2023): 1077. http://dx.doi.org/10.3390/met13061077.

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Lewandowski, Andrzej, Leszek Loroch i Monika Świech. "Individual Protection of Aircraft as an Essential Factor of Flying in Conflict Zones and Terrorist Threat Areas". Journal of Konbin 7, nr 4 (1.01.2008): 71–93. http://dx.doi.org/10.2478/v10040-008-0080-0.

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Individual Protection of Aircraft as an Essential Factor of Flying in Conflict Zones and Terrorist Threat Areas The paper presents ground-to-air weapon threats for aircraft, especially regarding man-portable air-defense systems (MANPADS) and the methods for reducing the threats. Polish participation in military conflicts along with international terrorism result in increasing threats for aircraft. The conducted analysis result in efforts for providing individual protection of aircraft and new countermeasures. Employment of these systems on military aircraft contributes to improved flight safety in threat areas, however expensiveness of individual protection systems make them uncommon on civil aircraft.

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Estey, Ralph H. "Canadian use of aircraft for plant protection". Phytoprotection 85, nr 1 (27.08.2004): 7–12. http://dx.doi.org/10.7202/008900ar.

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AbstractSince 1912, Canadians have used aircraft as aids in the protection of field crops, orchards, and forests from the ravages of fungi, insects, frost, and fire. At first, only fixed-wing aircraft could be used, but from 1947 both fixed-wing and rotary-wing aircraft have been employed. This review also relates the involvement of pioneering people and companies that have developed aerial control methods against biotic and abiotic agents damaging to our plants.

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Zhang, Teng, Tianyu Zhang, Yuting He, Bo Hou i Changfan Li. "Principle and Method for Determining the Calendar Safety Life of Aircraft Structural Protection Systems". Coatings 13, nr 6 (24.05.2023): 976. http://dx.doi.org/10.3390/coatings13060976.

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The calendar safety life of the surface protection system in aircraft structures is the time limit for it to be used without functional failure at a certain level of reliability and confidence. The reliability of such protection systems and the operational safety and economy of the structure are closely related. This paper firstly establishes two methods for determining the calendar safety life of aircraft structural protection systems under a single service environment and in multiple service environments. A method for determining the reliability of the calendar safety life of the aircraft structural protection system was proposed, and an expression of the relationship between the maintenance costs for the aircraft fleet and the reliability of the calendar safety life of the aircraft structural protection system based on the relationship between the amount of corrosion damage to the structural substrate and the corrosion time and the expression of the calendar safety life of the protection system was established. Finally, taking a hypothetical aircraft fuselage wall plate connection structure as an example, an alternating corrosion fatigue test with protection system specimens was carried out. The process for determining the calendar safety life of the structural protection system and its reliability are given. This method is important to ensure the safety of aircraft structures, improve the efficiency of use, and reduce maintenance costs. Generally speaking, the reliability of the calendar safety life of the structure is 99.9%, and after the analysis in this paper, the reliability of the structural protection system is about 70%.

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Bardaro, Danilo, Alessandro Bozzolo i Donato Zangani. "Advanced Technologies for Bombproof Cargo Containers and Blast Containment Units for the Retrofitting of Passenger Airplanes". International Journal of Aviation Systems, Operations and Training 2, nr 1 (styczeń 2015): 33–47. http://dx.doi.org/10.4018/ijasot.2015010103.

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Commercial aviation can be protected from the threat of explosives in two ways, either by preventing explosives from reaching the aircraft or by mitigating the effects of an explosive by protecting the aircraft from an onboard explosion. The containment units under study aim at acting as complementary and passive security measures for passengers and cabin crew. The proposed concept is a container where an internal high strength layer made of ballistic textiles is used to stop blast fragments, coupled with an external layer deforming in a controlled way during the explosion, designed to fully contain the blast pressure. The current research builds upon the positive results of such concept from a campaign of blast tests and extending its application by developing solutions for the protection of wide-body aircrafts and addressing the Least Risk Bomb Location (LRBL) directive.

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Luo, Hong. "Lightning Protection Design of Transceiver Based on Radio Altimeter". Architecture Engineering and Science 3, nr 2 (5.07.2022): 151. http://dx.doi.org/10.32629/aes.v3i2.899.

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Lightning is a great threat to aircraft flight safety. The lightning protection test of aircraft and the ability of aircraft and its parts to withstand direct and indirect effects are investigated and verified by simulating the real lightning environment in the laboratory. According to the requirements of GJB lightning test, this paper analyzes the lightning grade and introduces several lightning protection designs commonly used in engineer practice.

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Zaitseva, Alina, Nikolai Dudayev i Konstantin Shcherbakov. "MICROPROCESSOR SYSTEM FOR AUTOMATIC CONTROL OF AIRCRAFT FIRE PROTECTION MEANS". Electrical and data processing facilities and systems 18, nr 1 (2022): 131–42. http://dx.doi.org/10.17122/1999-5458-2022-18-1-131-142.

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Relevance The ever-increasing requirements for the safety of the use of aviation technology are inextricably linked with the problem of providing fire protection for aircraft, both military and civilian. The complexity of the problem of ensuring the fire safety of flights is associated with an increase in the intensity of the use of aviation equipment and the expansion of the range of functional tasks performed by it. The resulting complication of on-board equipment and an increase in the number of energy-intensive devices creates the prerequisites for the occurrence of fires on board the aircraft. At the same time, the remoteness of places where fires are possible, the variety of causes leading to fires, as well as the ambiguity of the conditions for the onset and spread, increase the likelihood of equipment failures, but also complicate the crew's activities. The purpose of the study is to implement a prospective aircraft fire protection system that will increase the effectiveness of existing fire extinguishing equipment. The relevance of this research project lies in the creation of an aircraft fire-fighting system that will provide timely detection of overheating/fire in the nacelles of the main power unit, in the compartments of the auxiliary power unit, baggage and cargo compartments and aircraft toilets; reliability of information from fire detection and elimination systems; increase the effectiveness of existing firefighting equipment. Aim of research The aim of the study is to develop a future aircraft fire protection system that will increase the effectiveness of existing fire extinguishing equipment. The objectives of the research project are: 1. Choosing a hardware complex for electronic indication and signaling of the aircraft fire-fighting system; 2. Integration of the fire protection complex into the general aircraft equipment control system. Research methods Analysis of modern high-performance aircraft fire protection systems and creation of a promising fire protection system based on the data obtained Results In the course of this research project, a hardware complex for electronic indication and signaling of the aircraft fire system was selected, and the integration of the fire protection complex into the control system of general aircraft equipment was carried out.

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Rozprawy doktorskie na temat "Aircraft protection"

Unnikrishnan, Suraj. "Adaptive Envelope Protection Methods for Aircraft". Diss., Georgia Institute of Technology, 2006. http://hdl.handle.net/1853/11478.

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Carefree handling refers to the ability of a pilot to operate an aircraft without the need to continuously monitor aircraft operating limits. At the heart of all carefree handling or maneuvering systems, also referred to as envelope protection systems, are algorithms and methods for predicting future limit violations. Recently, envelope protection methods that have gained more acceptance, translate limit proximity information to its equivalent in the control channel. Envelope protection algorithms either use very small prediction horizon or are static methods with no capability to adapt to changes in system configurations. Adaptive approaches maximizing prediction horizon such as dynamic trim, are only applicable to steady-state-response critical limit parameters. In this thesis, a new adaptive envelope protection method is developed that is applicable to steady-state and transient response critical limit parameters. The approach is based upon devising the most aggressive optimal control profile to the limit boundary and using it to compute control limits. Pilot-in-the-loop evaluations of the proposed approach are conducted at the Georgia Tech Carefree Maneuver lab for transient longitudinal hub moment limit protection. Carefree maneuvering is the dual of carefree handling in the realm of autonomous Uninhabited Aerial Vehicles (UAVs). Designing a flight control system to fully and effectively utilize the operational flight envelope is very difficult. With the increasing role and demands for extreme maneuverability there is a need for developing envelope protection methods for autonomous UAVs. In this thesis, a full-authority automatic envelope protection method is proposed for limit protection in UAVs. The approach uses adaptive estimate of limit parameter dynamics and finite-time horizon predictions to detect impending limit boundary violations. Limit violations are prevented by treating the limit boundary as an obstacle and by correcting nominal control/command inputs to track a limit parameter safe-response profile near the limit boundary. The method is evaluated using software-in-the-loop and flight evaluations on the Georgia Tech unmanned rotorcraft platform- GTMax. The thesis also develops and evaluates an extension for calculating control margins based on restricting limit parameter response aggressiveness near the limit boundary.

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Sears, Joanne Marie. "An investigation of aluminium-magnesium-cerium alloy coatings for corrosion protection". Thesis, University of Salford, 2001. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.365974.

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Rea, S. P. "Electromagnetic interference investigation and protection methods for HIRF in aircraft engine nacelle structures". Thesis, Queen's University Belfast, 2005. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.426585.

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Chaganti, Pradeep. "PROTECTION OF CARBON/CARBON AIRCRAFT BRAKES FROM OXIDATION USING PHOSPHOROUS BASED ANTI-OXIDANT SYSTEM". OpenSIUC, 2011. https://opensiuc.lib.siu.edu/theses/644.

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Carbon/Carbon (C/C) composite is defined as a carbon fiber reinforced carbon matrix. Since 1958 research has been carried out on the C/C composites. The main reason for the development of new C/C composites is the number of advantages it has to offer when compared with the regular materials. The areas where C/C composites are being used extensively are aerospace, military, etc. These C/C composites have better physical, mechanical, thermal properties when compared to steel. That is the reason C/C brakes made a huge impact in the aerospace industry. The main drawback associated with the C/C brakes which are used in aerospace applications is the oxidation of the composite at higher temperatures. Also other problem linked with the C/C brake is the migration of the inhibitors on to the friction surface of the brake which can eventually decrease the friction coefficient of the brake material. So, characterizing the commercially available Anti-Oxidant(A/O) system, developing a new A/O system which can not only provide better oxidation protection, but also an improved anti-oxidant migration resistance will be our main goal of this project.

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Bates, Robin Ian. "Corrosion protection of aircraft fasteners : alternatives to electroplated cadmium by closed field unbalanced magnetron sputtering". Thesis, University of Salford, 2000. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.365991.

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Telford, Rory. "Novel methods for improving fault protection & health management within advanced aircraft electrical power systems". Thesis, University of Strathclyde, 2017. http://digitool.lib.strath.ac.uk:80/R/?func=dbin-jump-full&object_id=27950.

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The more-electric aircraft (MEA) concept is widely viewed as the next evolutionary step towards enabling the industry goal of developing optimised, fuel efficient aircraft. MEA have an increased dependency on electrical energy for distribution to secondary systems and, in order to service this increased dependence, the electrical power systems (EPS) are more complex with increased voltage distribution levels, power conversion stages and safety critical components compared with their conventional counterparts. These complexities will only increase in future platforms as they further embrace the MEA concept - the migration to increasingly novel, critical and complex EPS will incur several development and integration challenges. This thesis considers the fundamental challenge of maintaining high reliability standards within future aircraft EPS through the development of accurate and discriminative real-time protection systems which will react during fault conditions. Specifically, the thesis researches novel methods that improve real-time aircraft EPS protection and health management systems by 1) accurately diagnosing degraded faults before their progression to critical failure and 2) diagnosing faults that are difficult to detect using only conventional protection methods â in particular, series arc faults are considered. Within future aircraft EPS, the volume of operational data is expected to significantly increase beyond that of the conventional systems; consequently, the thesis focuses on the use of data-driven, machine learning based methods, to enable these extended functionalities of the EPS protection and health management systems. The types of machine learning modelling techniques that were chosen are explained and justified. Conventional protection methods are described, including a discussion on the difficulties in using them to detect both degraded fault modes and arcing conditions. The necessity to detect these types of faults in an accurate and timely manner is also discussed. One of the main contributions of the thesis is the proposal of the EPSmart method that can autonomously diagnose and isolate a multitude of degraded faults within an aircraft representative EPS. These degraded faults include intermittent and incipient conditions, which, in comparison to overcurrent faults, often lack the energy to be detected by conventional means. Early, and accurate, detection of these conditions will improve overall system health management and reliability and ensure safe operation of the aircraft. Further contribution is the design of the IntelArc method that can detect series arc faults within direct current supplied systems. Accurate detection of series arc faults is extremely challenging as, despite their presence being a serious fire hazard, they result in a decrease of load current. Although methods do exist for diagnosis of series arcing, there remain challenges with regards to accurate detection across different system configurations and operating conditions. The thesis shows the potential for IntelArc to provide accurate detection across a variety of configurations and operating conditions. While the thesis only describes the initial development of these novel methods, the significant conclusions are that application testing has shown the potential for them to enhance real-time network protection, fault tolerance and health management of aircraft EPS through detection of degraded fault and arcing conditions.

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Costain, Andrew J. "The development and analysis of a mobile explosive containment unit for on-board aircraft protection". Thesis, Virginia Tech, 2014. http://hdl.handle.net/10919/50521.

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This body of work examines the process involved in researching a mobile explosive containment unit for use on board a commercial aircraft. If a device with unknown origin were discovered on board a commercial aircraft an explosive containment unit could be used to dispose of it thereby preventing the passengers and the hardware from incurring any harm. A methodology was developed to help understand and effectively capture the properties of nominal explosives, the detonation pulse, ensuing shock and pressure waves. This methodology was developed with the purpose of mitigating these explosive effects. The information concerning the material properties, shape and sizes of an explosive containment unit were all analyzed to identify one optimal containment unit. This containment unit was utilized extensively in modeling to determine a range of possible materials and reinforcement methods, for reducing the total weight of the unit. Upon optimizing the containment unit numerical analysis was performed on a fuselage section of a narrow body commercial aircraft with the containment unit. The containment unit was successful in arresting the explosion before it was able to cause harm to its surroundings. The success of these containment units proves that the methodology discussed and developed here is capable of rabidly developing and analyzing explosive containment units to fit a wide variety of needs.
Master of Science

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Baillio, Sarah S. "Corrosion Protection of Aerospace Grade Magnesium Alloy Elektron 43™ for Use in Aircraft Cabin Interiors". Thesis, University of North Texas, 2013. https://digital.library.unt.edu/ark:/67531/metadc283846/.

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Magnesium alloys exhibit desirable properties for use in transportation technology. In particular, the low density and high specific strength of these alloys is of interest to the aerospace community. However, the concerns of flammability and susceptibility to corrosion have limited the use of magnesium alloys within the aircraft cabin. This work studies a magnesium alloy containing rare earth elements designed to increase resistance to ignition while lowering rate of corrosion. The microstructure of the alloy was documented using scanning electron microscopy. Specimens underwent salt spray testing and the corrosion products were examined using energy dispersive spectroscopy.

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Imbayan, Mike. "DEVELOPMENT OF SILLICON BASED OVERCOAT FOR HIGH TEMPERATURE OXIDATION PROTECTION OF CARBON-CARBON COMPOSITES AIRCRAFT BRAKE". OpenSIUC, 2015. https://opensiuc.lib.siu.edu/theses/1680.

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Much research of Anti-Oxidant has been developed and is still being developed to protect Carbon-Carbon(C/C) material from oxidizing. C/C materials tend to lose their mechanical properties due to the oxidation. The aerospace brake industries have conducted a lot of research on this, because C/C material is an excellent material to be used for brake systems if a good oxygen protection is developed for it. The research performed by Dr.Jarlen Don detected a problem with the oxidation at high temperatures with the current composition. Phosphorus based coating does not protect C/C for more than 15 hours at 871C. By doing a multi-layer coating of the anti-oxidant, the anti-oxidant will be able to protect the brake systems better at a high temperature. To address the problem, research and experiments were conducted to protect oxidation at higher temperatures by using a silicon-based anti-oxidant. Silicon based overcoat will be the top layer of the anti-oxidant while the bottom will be the phosphorus based anti-oxidant that previously has been coated.

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Yildiz, Bahri. "Exploration of the use of unmanned aerial vehicles along with other assets to enhance border protection". Thesis, Monterey, Calif. : Naval Postgraduate School, 2009. http://edocs.nps.edu/npspubs/scholarly/theses/2009/Jun/09Jun%5FYildiz.pdf.

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Thesis (M.S. in Operations Research)--Naval Postgraduate School, June 2009.
Thesis Advisor(s): Horne, Gary E. "June 2009." Description based on title screen as viewed on July 13, 2009. Author(s) subject terms: border security, border protection, border patrol, unmanned aerial system (UAS), UAV, MANA, Nearly-Orthogonal Latin Hypercube, regression tree, linear regression. Includes bibliographical references (p. 89-93). Also available in print.

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Książki na temat "Aircraft protection"

Birch, N. H. Passenger protection technology in aircraft accident fires. Aldershot: Gower Technical, 1988.

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Birch, Neville Hamilton. Passenger protection technology in aircraft accident fires. Aldershot, Hants, England: Gower Technical Press, 1988.

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S, Narayanaswamy, i United States. National Aeronautics and Space Administration., red. Integrator windup protection: Techniques and a STOVL aircraft engine controller application : final report. [Washington, DC: National Aeronautics and Space Administration, 1997.

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B, Walen D., i Langley Research Center, red. Consistent approach to describing aircraft HIRF protection: Contract NAS1-19360. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

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Docherty, Robert W. Airports and aircraft fire protection, fire fighting and rescue techniques. Leicester: Institution of Fire Engineers, 1990.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Neck injury in advanced military aircraft environments. Neuilly sur Seine, France: AGARD, 1990.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Neck injury in advanced military aircraft environments. Neuilly-sur-Seine: AGARD, 1990.

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Smith, D. P. Aircraft cargo bay fire protection by water sprays: A feasibility study. Cheltenham: Civil Aviation Authority, 1993.

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Wilson, J. W. Radiation safety issues in high altitude commercial aircraft. [Washington, D.C: National Aeronautics and Space Administration, 1995.

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United States. Environmental Protection Agency. Science Advisory Board i United States. Environmental Protection Agency. Office of the Administrator, red. Consultation on EPA's proposed aircraft drinking water rule (ADWR). Washington, DC: U.S. Environmental Protection Agency, Office of the Administrator, Science Advisory Board, 2008.

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Części książek na temat "Aircraft protection"

Lankarani, H. M. "Current Issues Regarding Aircraft Crash Injury Protection". W Crashworthiness of Transportation Systems: Structural Impact and Occupant Protection, 579–612. Dordrecht: Springer Netherlands, 1997. http://dx.doi.org/10.1007/978-94-011-5796-4_21.

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Cifaldi, Carmine. "Unmanned Aircraft System Privacy and Data Protection". W Handbook of Unmanned Aerial Vehicles, 1–19. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-32193-6_158-1.

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Gooch, Jan W., i John K. Daher. "Field Test Evaluations on E-3A Aircraft". W Electromagnetic Shielding and Corrosion Protection for Aerospace Vehicles, 57–74. New York, NY: Springer New York, 2007. http://dx.doi.org/10.1007/978-0-387-46096-3_6.

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Kindervater, C. M. "Aircraft and Helicopter Crashworthiness: Design and Simulation". W Crashworthiness of Transportation Systems: Structural Impact and Occupant Protection, 525–77. Dordrecht: Springer Netherlands, 1997. http://dx.doi.org/10.1007/978-94-011-5796-4_20.

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Chary, Charles. "Development and Validation of a Bird Strike Protection System for an Enhanced Adaptive Droop Nose". W Smart Intelligent Aircraft Structures (SARISTU), 71–83. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-22413-8_3.

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Yang, Lufan, i Zheng Chen. "Dynamic Weapon-Target Assignment for Active Protection of Aircraft". W Proceedings of 2021 5th Chinese Conference on Swarm Intelligence and Cooperative Control, 1214–24. Singapore: Springer Nature Singapore, 2022. http://dx.doi.org/10.1007/978-981-19-3998-3_115.

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Fisher, Joseph, Paul R. P. Hoole, Kandasamy Pirapaharan i Samuel R. H. Hoole. "Lightning Electrodynamics: Electric Power Systems and Aircraft". W Lightning Engineering: Physics, Computer-based Test-bed, Protection of Ground and Airborne Systems, 233–88. Cham: Springer International Publishing, 2022. http://dx.doi.org/10.1007/978-3-030-94728-6_7.

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Hintze, Hartmut, Benjamin Wiegraefe i Ralf God. "A Security Engineering Process Approach for the Future Development of Complex Aircraft Cabin Systems". W Security and Privacy Protection in Information Processing Systems, 190–202. Berlin, Heidelberg: Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-39218-4_15.

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Kidun, Elizaveta S., i Natalia A. Volgina. "Russian Aircraft “Sukhoi Superjet-100”: Position in Russian and Global Markets". W Towards an Increased Security: Green Innovations, Intellectual Property Protection and Information Security, 649–57. Cham: Springer International Publishing, 2022. http://dx.doi.org/10.1007/978-3-030-93155-1_70.

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Kun, Han, i Zhu Hongyu. "Human Error Related Design of Fire Protection Control System in Civil Aircraft Cockpit". W Advances in Intelligent Systems and Computing, 516–23. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-68017-6_77.

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Streszczenia konferencji na temat "Aircraft protection"

DELUCA, J., B. FENTON, S. PETRIE i J. SALVINO. "Lightweight aircraft turbine protection". W 29th Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-1815.

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Case, Jr., Russell L., i Peter H. Wolff. "Commercial-Aircraft Protection System". W Defense and Security, redaktor Edward M. Carapezza. SPIE, 2004. http://dx.doi.org/10.1117/12.540673.

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Simon, Albert J. "Raytheon aircraft protection systems". W Defense and Security Symposium, redaktorzy Theodore T. Saito i Daniel Lehrfeld. SPIE, 2006. http://dx.doi.org/10.1117/12.666534.

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Treacy, James J. "AIRCRAFT CERTIFICATION: HIRF PROTECTION REQUIREMENTS FOR CIVIL AIRCRAFT SYSTEMS". W Aerospace Technology Conference and Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1990. http://dx.doi.org/10.4271/901918.

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Norman, Patrick, Stuart Galloway, Graeme Burt i Jason Hill. "Adaptive Protection Methods for Aircraft Applications". W Power Systems Conference. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2010. http://dx.doi.org/10.4271/2010-01-1750.

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Well, Klaus. "Aircraft Control Laws for Envelope Protection". W AIAA Guidance, Navigation, and Control Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-6055.

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Zheng, Sizhuang, Lixin Wang, Ting Yue i Hailiang Liu. "Envelope Protection Reconfiguration for Iced Aircraft". W 2021 12th International Conference on Mechanical and Aerospace Engineering (ICMAE). IEEE, 2021. http://dx.doi.org/10.1109/icmae52228.2021.9522446.

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Fuiorea, Ion, Tudor Chereches i Paul Lixandru. "Aircraft ballistic protection trade off studies". W 2017 International Conference on Military Technologies (ICMT). IEEE, 2017. http://dx.doi.org/10.1109/miltechs.2017.7988814.

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Brice, D., i M. Reed. "Challenges in the lightning protection of aircraft wire and cable installations on composite aircraft". W IET Seminar on Lightning Protection for Aircraft Components. Institution of Engineering and Technology, 2013. http://dx.doi.org/10.1049/ic.2013.0176.

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Fisher, J., P. R. P. Hoole, K. Pirapaharan, S. Thirukumaran i S. R. H. Hoole. "Three dimensional electric dipole model for lightning-aircraft electrodynamics and its application to low flying aircraft". W 2014 International Conference on Lightning Protection (ICLP). IEEE, 2014. http://dx.doi.org/10.1109/iclp.2014.6973163.

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Raporty organizacyjne na temat "Aircraft protection"

Ehst, David A. Commercial Aircraft Protection. Office of Scientific and Technical Information (OSTI), październik 2016. http://dx.doi.org/10.2172/1346573.

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Kotov, Nicholas A. Advanced Nanostructured Hybrid Coatings for the Protection of Aircraft. Fort Belvoir, VA: Defense Technical Information Center, październik 2005. http://dx.doi.org/10.21236/ada438246.

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Bierwagen, Gordon P., Dennis E. Tallman, Stuart Croll, Philip Boudjouk i Victoria J. Gelling. Corrosion Protection of Aluminum Alloys Used in Aircraft - Testing, Analysis and Development of Environmentally Compliant Coatings and Pretreatments for the Corrosion Protection of Aircraft Alloys. Fort Belvoir, VA: Defense Technical Information Center, wrzesień 2002. http://dx.doi.org/10.21236/ada417676.

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Hanlon, Walker, i Taylor Jaworski. Spillover Effects of IP Protection in the Inter-war Aircraft Industry. Cambridge, MA: National Bureau of Economic Research, listopad 2019. http://dx.doi.org/10.3386/w26490.

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Centrone, John A., Harold D. Beeson, J. K. Newman, Thomas J. Stepetic, Billy Dees, Keith Moser i Joseph L. Walker. Fire Protection and Detection System: Hardened Aircraft Shelter (HAS) Personnel Egress and Fuel Securing. Fort Belvoir, VA: Defense Technical Information Center, lipiec 1988. http://dx.doi.org/10.21236/ada577879.

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Murty, Gollapudi S., i Arvind Agarwal. Development of Spray Coating Methods and Materials to Replace Aluminum Cladding of Aging Aircraft for Corrosion Protection. Fort Belvoir, VA: Defense Technical Information Center, czerwiec 2007. http://dx.doi.org/10.21236/ada470203.

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Barzen, Jeb, i Ken Ballinger. Sandhill and Whooping Cranes. U.S. Department of Agriculture, Animal and Plant Health Inspection Service, styczeń 2017. http://dx.doi.org/10.32747/2017.7207736.ws.

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As sandhill crane populations continue to grow in the United States, so too does crop damage, property damage to homeowners, and the risk of crane collisions with aircraft. Whooping crane populations also continue to grow, but with a global population of about 500 individuals (as of 2017), damage is rare and problems often require different solutions due to the species’ endangered status. The sandhill crane (Grus canadensis), is a long-lived, member of the crane family (Gruidae) and the most numerous of the 15 crane species found worldwide. Over the last 50 years, the species has grown from a rarity─ requiring extensive protection─ to an abundant, widespread species. As their populations have increased, so too have their conflicts with people. Both sandhill and whooping cranes are protected under the Migratory Bird Treaty Act (MBTA) of 1918. This law strictly prohibits the capture, killing, or possession of sandhill and whooping cranes without proper permits. However, the U.S. Fish and Wildlife Service (USFWS) can issue depredation permits under this act for the shooting of sandhill cranes that causeagricultural damage or threaten human health and safety. No federal permit is required to use non-lethal management methods to reduce damage by sandhill cranes.

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Grenich, A. F. Vulnerability Methodology and Protective Measures for Aircraft Fire and Explosion Hazards. Volume 1. Executive Summary. Fort Belvoir, VA: Defense Technical Information Center, styczeń 1986. http://dx.doi.org/10.21236/ada167443.

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Desmarais, L. A., W. J. Yagle i A. F. Grenich. Vulnerability Methodology and Protective Measures for Aircraft Fire and Explosion Hazards. Volume 3. On-Board Inert Gas Generator System (OBIGGS) studies. Part 3. Aircraft OBIGGS Designs. Fort Belvoir, VA: Defense Technical Information Center, styczeń 1986. http://dx.doi.org/10.21236/ada185282.

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Job, Jacob. Mesa Verde National Park: Acoustic monitoring report. National Park Service, lipiec 2021. http://dx.doi.org/10.36967/nrr-2286703.

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In 2015, the Natural Sounds and Night Skies Division (NSNSD) received a request to collect baseline acoustical data at Mesa Verde National Park (MEVE). Between July and August 2015, as well as February and March 2016, three acoustical monitoring systems were deployed throughout the park, however one site (MEVE002) stopped recording after a couple days during the summer due to wildlife interference. The goal of the study was to establish a baseline soundscape inventory of backcountry and frontcountry sites within the park. This inventory will be used to establish indicators and thresholds of soundscape quality that will support the park and NSNSD in developing a comprehensive approach to protecting the acoustic environment through soundscape management planning. Additionally, results of this study will help the park identify major sources of noise within the park, as well as provide a baseline understanding of the acoustical environment as a whole for use in potential future comparative studies. In this deployment, sound pressure level (SPL) was measured continuously every second by a calibrated sound level meter. Other equipment included an anemometer to collect wind speed and a digital audio recorder collecting continuous recordings to document sound sources. In this document, “sound pressure level” refers to broadband (12.5 Hz–20 kHz), A-weighted, 1-second time averaged sound level (LAeq, 1s), and hereafter referred to as “sound level.” Sound levels are measured on a logarithmic scale relative to the reference sound pressure for atmospheric sources, 20 μPa. The logarithmic scale is a useful way to express the wide range of sound pressures perceived by the human ear. Sound levels are reported in decibels (dB). A-weighting is applied to sound levels in order to account for the response of the human ear (Harris, 1998). To approximate human hearing sensitivity, A-weighting discounts sounds below 1 kHz and above 6 kHz. Trained technicians calculated time audible metrics after monitoring was complete. See Methods section for protocol details, equipment specifications, and metric calculations. Median existing (LA50) and natural ambient (LAnat) metrics are also reported for daytime (7:00–19:00) and nighttime (19:00–7:00). Prominent noise sources at the two backcountry sites (MEVE001 and MEVE002) included vehicles and aircraft, while building and vehicle predominated at the frontcountry site (MEVE003). Table 1 displays time audible values for each of these noise sources during the monitoring period, as well as ambient sound levels. In determining the current conditions of an acoustical environment, it is informative to examine how often sound levels exceed certain values. Table 2 reports the percent of time that measured levels at the three monitoring locations were above four key values.

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