Relevant bibliographies by topics / Helicopter transmissions

Contents

  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Helicopter transmissions'

Author: Grafiati
Published: 4 June 2021
Last updated: 5 February 2022

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Journal articles on the topic "Helicopter transmissions"

1

Haiwei, Wang, Li Lulu, and Yuan Sheng. "Research on Rapid Assembly Technology of Helicopter Transmissions." MATEC Web of Conferences 306 (2020): 05004. http://dx.doi.org/10.1051/matecconf/202030605004.

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Research and application of rapid assembly technology can widely improve the design efficiency of helicopter transmissions. An assembly model of helicopter transmissions is presented by introducing Geometric Constraint Graph (GCG) method. A hierarchical model is obtained by multi-shrink decomposition. A corresponding data structure is generated according to the hierarchical model. CATIA based a parametric component database is built up. The Assembly modelling software is implemented by using VB. Finally, a helicopter transmissions example is taken as application and the rapid assembly for helicopter transmission system is achieved.
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Davies, D. P., and B. C. Gittos. "Gear Steels for Future Helicopter Transmissions." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 203, no. 2 (July 1989): 113–21. http://dx.doi.org/10.1243/pime_proc_1989_203_062_01.

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In order to reduce weight, improve reliability and increase safety, significant changes in the design of future helicopter transmissions are envisaged. Such designs are likely to place new demands on conventional steels which will eventually result in the capability of the gear steels themselves to become the limiting factor, restricting any further opportunities for transmission design and development.
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Xue, Hui Ling, Geng Liu, Xiao Hui Yang, and Bing Han. "Key Technologies Research of Helicopter Transmissions." Applied Mechanics and Materials 743 (March 2015): 55–60. http://dx.doi.org/10.4028/www.scientific.net/amm.743.55.

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In the recent years, there has been significant interest in the new developments and improvements of the helicopter transmission systems. The main goal of the helicopter transmission research is the reduction of overall gear train weight while maintaining the efficiency and reliability. This paper reviews some significant technical developments in the component level and in the system configuration level. In addition, comprehensive test and verification technology of helicopter transmission system is discussed.
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Litvin, F. L., J. C. Wang, R. B. Bossler, Y. J. D. Chen, G. Heath, and D. G. Lewicki. "Application of Face-Gear Drives in Helicopter Transmissions." Journal of Mechanical Design 116, no. 3 (September 1, 1994): 672–76. http://dx.doi.org/10.1115/1.2919434.

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The use of face-gears in helicopter transmissions was explored. A light-weight, split torque transmission design utilizing face-gears was described. Face-gear design is discussed. Topics included basic design geometry, tooth generation, limiting inner and outer radii, and recommendation for the gear ratio. Face-gear experimental studies were also included and the feasibility of face-gears in high-speed, high-load applications such as helicopter transmissions was demonstrated. Torque-split tests were performed and demonstrated an accurate split of torque using the face-gear concept.
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White, G. "Split Torque Helicopter Transmissions with Widely Separated Engines." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 203, no. 1 (January 1989): 53–65. http://dx.doi.org/10.1243/pime_proc_1989_203_054_01.

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A three-stage helicopter transmission of split torque type is shown to offer advances in a configuration that allows the engine axes to be widely separated and parallel. Three variants of the configuration are examined; one design with separated drive paths and four final-drive pinions is discussed in detail. This design offers 26 per cent less weight and 9 per cent lower losses than current production transmissions. Comparison is made with epicyclic type transmissions of similar rating that have been developed in the past decade.
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Ye, Qian. "Event-driven PID control of autonomous quadrotor helicopters." Journal of Algorithms & Computational Technology 12, no. 2 (March 7, 2018): 159–64. http://dx.doi.org/10.1177/1748301818761134.

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This paper proposes an event-driven PID control mechanism for autonomous quadrotor helicopters that will reduce the usage of communication channels. Compared to traditional PID controller, the event-driven PID controller can maintain the satisfactory stabilization effect with the ability of reducing the number of transmissions significantly. The simplified dynamics model of quadrotor helicopter is also established. Finally, the improvements realized by the developed method are verified in the computer simulations.
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Astridge, D. G. "Helicopter Transmissions—design for Safety and Reliability." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 203, no. 2 (July 1989): 123–38. http://dx.doi.org/10.1243/pime_proc_1989_203_063_01.

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Recent improvements in design and component technologies are reviewed against a background of accident data analysis, resulting in grounds for confidence in higher safety levels in future rotorcraft transmission designs. Recommendations are made concerning the realization of significant safety and reliability benefits afforded by effective health and usage monitoring systems. The results of this study are applicable to all new aerospace gearbox applications including helicopters, tilt-rotor aircraft, advanced propeller engines and accessory drive systems.
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Handschuh, R. F., D. G. Lewicki, and R. B. Bossler. "Experimental Testing of Prototype Face Gears for Helicopter Transmissions." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 208, no. 2 (July 1994): 129–36. http://dx.doi.org/10.1243/pime_proc_1994_208_262_02.

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An experimental programme to test the feasibility of using face gears in a high-speed and high-power environment was conducted. Four face gear sets were tested, two sets at a time, in a closed-loop test stand at pinion rotational speeds to 19 100 r/min and to 271 kW (364 b.h.p.). The test gear sets were one-half scale of the helicopter design gear set. Testing the gears at one-eighth power, the test gear set had slightly increased bending and compressive stresses when compared to the full-scale design. The tests were performed in the NASA Lewis spiral bevel gear test facility. All four sets of gears successfully ran at 100 per cent of design torque and speed for 30 million pinion cycles, and two sets successfully ran at 200 per cent of torque for an additional 30 million pinion cycles. The results, although limited, demonstrated the feasibility of using face gears for high-speed, high-load applications.
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Lewicki, David G., Robert F. Handschuh, Zachary S. Henry, and Faydor L. Litvin. "Low-noise, high-strength, spiral-bevel gears for helicopter transmissions." Journal of Propulsion and Power 10, no. 3 (May 1994): 356–61. http://dx.doi.org/10.2514/3.23764.

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Tumer, Irem Y., and Edward M. Huff. "Analysis of Triaxial Vibration Data for Health Monitoring of Helicopter Gearboxes." Journal of Vibration and Acoustics 125, no. 1 (January 1, 2003): 120–28. http://dx.doi.org/10.1115/1.1526130.

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Research on the nature of the vibration data collected from helicopter transmissions during flight experiments has led to several crucial observations believed to be responsible for the high rates of false alarms and missed detections in aircraft vibration monitoring systems. This work focuses on one such finding, namely, the need to consider additional sources of information about system vibrations. In this light, helicopter transmission vibration data, collected using triaxial accelerometers, are explored in three different directions, analyzed for content, and then combined using Principal Components Analysis (PCA) to analyze changes in directionality. The frequency content of the three different directions is compared and analyzed using time-synchronously averaged vibration data. To provide a method for analysis and monitoring purposes, the triaxial data are decorrelated using a mathematical transformation, and compared to the original axes to determine their differences. The benefits of using triaxial data for vibration monitoring and diagnostics are explored by analyzing the changes in the direction of the principal axis of vibration formed using all three axes of vibration. The statistical variation introduced due to the experimental variables is further analyzed using an Analysis of Variance approach to determine the effect of each variable on the overall signature. The results indicate that triaxial accelerometers can provide additional information about the frequency content of helicopter gearbox vibrations, and provide researchers and industry with a novel method of capturing and monitoring triaxial changes in the baseline vibration signatures.
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Dissertations / Theses on the topic "Helicopter transmissions"

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Patrick-Aldaco, Romano. "A Model Based Framework for Fault Diagnosis and Prognosis of Dynamical Systems with an Application to Helicopter Transmissions." Diss., Georgia Institute of Technology, 2007. http://hdl.handle.net/1853/16266.

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The thesis presents a framework for integrating models, simulation, and experimental data to diagnose incipient failure modes and prognosticate the remaining useful life of critical components, with an application to the main transmission of a helicopter. Although the helicopter example is used to illustrate the methodology presented, by appropriately adapting modules, the architecture can be applied to a variety of similar engineering systems. Models of the kind referenced are commonly referred to in the literature as physical or physics-based models. Such models utilize a mathematical description of some of the natural laws that govern system behaviors. The methodology presented considers separately the aspects of diagnosis and prognosis of engineering systems, but a similar generic framework is proposed for both. The methodology is tested and validated through comparison of results to data from experiments carried out on helicopters in operation and a test cell employing a prototypical helicopter gearbox. Two kinds of experiments have been used. The first one retrieved vibration data from several healthy and faulted aircraft transmissions in operation. The second is a seeded-fault damage-progression test providing gearbox vibration data and ground truth data of increasing crack lengths. For both kinds of experiments, vibration data were collected through a number of accelerometers mounted on the frame of the transmission gearbox. The applied architecture consists of modules with such key elements as the modeling of vibration signatures, extraction of descriptive vibratory features, finite element analysis of a gearbox component, and characterization of fracture progression. Contributions of the thesis include: (1) generic model-based fault diagnosis and failure prognosis methodologies, readily applicable to a dynamic large-scale mechanical system; (2) the characterization of the vibration signals of a class of complex rotary systems through model-based techniques; (3) a reverse engineering approach for fault identification using simulated vibration data; (4) the utilization of models of a faulted planetary gear transmission to classify descriptive system parameters either as fault-sensitive or fault-insensitive; and (5) guidelines for the integration of the model-based diagnosis and prognosis architectures into prognostic algorithms aimed at determining the remaining useful life of failing components.
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Buysschaert, Frank. "Helicopter power transmission : changing the paradigm." Thesis, University of Southampton, 2015. https://eprints.soton.ac.uk/386149/.

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In the conventional helicopter, the transmission and powerplant systems are the major production and operator direct operating cost drivers. Additionally, they are related to helicopter safety and reliability concerns and impose performance boundaries. As a consequence, they need to be addressed. Adapting the transmission and powerplant systems with the introduction of more electric technologies, which are reported to be more reliable and cost friendly, involves a gross weight penalty, which cannot be accepted from a performance viewpoint. The implementation of liquid hydrogen, with the objective to introduce a sustainable energy carrier and free cold source for the high temperature superconductive devices driving the tail rotor, appears unattractive, from either a weight or a exploitation standpoint. Biodiesel could be an alternative to Avgas driven configurations, but at the moment, it has questionable chemical characteristics and is therefore discarded. Conceptual alternatives to the conventional helicopter explored in an attempt to verify their ability to overcome the stated performance, safety and cost aspects, are subjected to the same problems, the Turbine Driven Rotor (TDR) helicopter configuration excepted. The TDR helicopter drives a coaxial rotor configuration by means of a rotor embedded Ljungstr¨om turbine, omitting the need for a mechanical transmission system. Three TDR helicopter thermodynamic cycles are proposed. The piston engine powered TDR cycle shows to be of interest for the low weight class helicopters. The turbofan powered TDR cycle is preferred in the mid and high weight categories, benefitting from its configurational simplicity. The more complex turboshaft powered TDR cycle requires a heat exchanger, is heavier and thus not recommended. With respect to the Ljungstrom turbine, the loss models of Soderberg and Ainley and Mathieson used to establish its geometry and performance characteristics are generally acceptable and appear coherent, while a deviation angle correction is developed to cope with the radial outflow configuration of the turbine. Similarly, loss models for the internal leakage and disk friction are proposed. However, these models could not be substantiated by means of experiments. A design methodology to implement the Ljungstrom turbine in the helicopter rotor head is presented and allows adjusting the thermodynamic cycle characteristics such as to maximise the performance gain with respect to the conventional helicopter. For nominal operating conditions, ISA SLS, a VLR-class TDR helicopter shows to bear a performance gain of 10% over a conventional helicopter when equipped with an Avgas engine and 14% when a Diesel engine is used. Hereby, the cycle pressure ratio remained low, i.e. approximately 1.25, allowing a turbine polytropic effciency of 87%. An identical study with a NH-90-class TDR helicopter proved to offer a performance potential of 50% at a cycle pressure ratio around 1.6 and a turbine polytropic effciency of 90%. In all cases, the gas temperature at the inlet of Ljungstrom turbine remained below the rotor bearing temperature limit of 400 K.
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Cioc, Carmen. "An elastohydrodynamic lubrication model for helicopter high-speed transmission components /." SeeFull Text at OhioLINK ETD Center (Requires Adobe Acrobat Reader for viewing), 2004. http://rave.ohiolink.edu/etdc/view?acc%5Fnum=toledo1100618919.

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Dissertation (Ph.D.)--University of Toledo, 2004.
Typescript. "A dissertation [submitted] as partial fulfillment of the requirements of the Doctor of Philosophy degree in Engineering." Bibliography: leaves 220-247.
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Cioc, Carmen Ana Beatrice. "An Elastohydrodynamic Lubrication Model for Helicopter High-Speed Transmission Components." University of Toledo / OhioLINK, 2004. http://rave.ohiolink.edu/etdc/view?acc_num=toledo1100618919.

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Roulois, Guillaume. "Etude et simulation du bruit des boîtes de transmission principales d'hélicoptères." Thesis, Dijon, 2011. http://www.theses.fr/2011DIJOS105.

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La boîte de transmission principale (BTP) est une des principales sources dubruit perçu dans les cabines d’hélicoptères et pénalise fortement le confort acoustique deséquipages et passagers. Afin de réduire l’impact de cette source, les phénomènes acoustiqueset vibratoires mis en jeu par les boîtes de transmission à engrenages doivent être compris etsimulés durant les phases de développement. De cette façon, le comportementvibroacoustique des BTP pourra être amélioré dès la conception, réduisant ainsi le coût, lamasse et les difficultés d’intégration des solutions d’insonorisation. Ce travail présente lesBTP d’hélicoptères ainsi que le bruit qu’elles génèrent. Il présente également nosdéveloppements concernant la modélisation du comportement dynamique des BTP afin d’encalculer le bruit. Nous avons développé un code éléments finis permettant d’effectuer desétudes paramétriques afin d’ajuster le design des boîtes de transmission lors des phases dedéveloppement. Notre modèle est capable de calculer les efforts dynamiques aux paliers detransmissions composées de plusieurs engrenages cylindriques et spiro-coniques. Enfin, nousanalysons des mesures acoustiques et vibratoires effectuées autour de deux BTP pourplusieurs conditions de couple et vitesse. Ces mesures nous permettent de mieux comprendrele comportement vibroacoustique des BTP et de confirmer certaines tendances observées avecnotre modèle
Main gearbox (MGB) is one of the main noise sources in helicopter cabinsand it strongly penalizes acoustic comfort of crews and passengers. In order to reduce theimpact of this source, acoustic and vibration mechanisms of gearboxes have to be understoodand simulated during the development phases. By this way, MGB vibroacoustic behaviourcould be improved by design, thus reducing cost, additional weight and integration difficultiesof sound-proofing solutions. This work presents helicopters MGB and the noise they generate.It also presents our developments regarding the modelling of MGB dynamic behaviour fornoise computation. We have developed a finite elements code allowing to conduct parametricstudies to tune the gearboxes design in early development phases. Our model is able tocompute dynamic loads on bearings of any transmission composed of several cylindrical andspiral bevel gears. At last, we analyse acoustic and vibration measurements done around twoMGB for several conditions of torque and speed. These measurements allow to betterunderstand MGB vibroacoustic behaviour and to confirm some trends observed with ourmodel
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Anderson, Gregory L. "Classification analysis of vibration data from SH-60B Helicopter Transmission Test Facility." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1997. http://handle.dtic.mil/100.2/ADA340978.

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Thesis (M.S. in Operations Research) Naval Postgraduate School, September 1997.
"September 1997." Thesis advisor(s): Robert R. Read. Includes bibliography references (p. 65). Also available online.
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Rovenstine, Michael J. "Classification analysis of vibration data from SH-60B Helicopter Transmission Test Facility." Monterey, California. Naval Postgraduate School, 1997. http://hdl.handle.net/10945/8087.

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Approved for public release; distribution is unlimited
Health and Usage Monitoring Systems (HUMS) is an emerging technology in helicopter aviation. The United States Navy is evaluating its viability for use on its helicopter fleet. HUMS uses sensors placed throughout the helicopter to monitor and record vibration signals and numerous other aircraft operating parameters. This thesis evaluates the vibration signals recorded by a HUMS system using a statistical technique called tree structured classification. The goal of the analysis is to demonstrate the technique's ability to predict the presence of faulted components in the transmission of the SH-60B autonomously operated in a Helicopter Transmission Test Facility at Naval Air Warfare Center, Trenton, New Jersey. The analysis is implemented in the statistical software package S-plus (Mathsoft Inc., 1995)
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Stevens, David John. "Review of Alternative Construction Methods for Transmission Towers." Thesis, University of Canterbury. Management, Marketing, and Entrepreneurship, 2014. http://hdl.handle.net/10092/8937.

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It is important to ensure that Transpower is prepared to deliver upcoming transmission tower refurbishment projects that are located on sites with difficult access. This project reviews the availability, capability and cost of utilising alternative construction methods and any associated wider issues. The focus of this report is on how Transpower can more effectively utilise helicopters and gin poles for transmission tower erection and material delivery on remote sites.
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Saribay, Zihni Burçay Smith Edward C. Rao Suren B. Bill Robert C. Wang K. W. "Analytical investigation of the pericyclic variable-speed transmission system for helicopter main-gearbox." [University Park, Pa.] : Pennsylvania State University, 2009. http://etda.libraries.psu.edu/theses/approved/WorldWideIndex/ETD-4689/index.html.

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Bellocchio, Andrew Thomas. "Drive System Design Methodology for a Single Main Rotor Helicopter." Thesis, Georgia Institute of Technology, 2005. http://hdl.handle.net/1853/7524.

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The transformation of Joint forces to be lighter, more lethal, and capable of deploying from multiple dispersed locations free of prepared landing zones requires a dedicated heavy lift VTOL aircraft capable of rapidly delivering large payloads, such as the 20 to 26 ton Future Combat System, at extended ranges in demanding terrain and environmental conditions. Current estimates for a single main rotor configuration place the design weight over 130,000 pounds with an installed power of approximately 30,000 horsepower. Helicopter drive systems capable of delivering torque of this magnitude succeeded in the Russian Mi-26 helicopters split-torque design and the Boeing VERTOL Heavy Lift Helicopter (HLH) prototypes traditional multi-stage planetary design. The square-cube law and historical trends show that the transmission stage weight varies approximately as the two-thirds power of torque; hence, as the size and weight of the vehicle grows, the transmissions weight becomes an ever-increasing portion of total gross weight. At this scale, optimal gearbox configuration and component design holds great potential to save significant weight and reduce the required installed power. The drive system design methodology creates a set of integrated tools to estimate system weight and rapidly model the preliminary design of drives system components. Tools are provided for gearbox weight estimation and efficiency, gearing, shafting, and cooling. Within the same architecture, the designer may add similar tools to model subcomponents such as support bearings, gearbox housing, freewheeling units, and rotor brakes. Measuring the relationships between key design variables and system performance metrics reveals insight into the performance and behavior of a heavy lift drive system. A parametric study of select design variables is accomplished through an intelligent Design of Experiments that utilizes Response Surface Methodology to build a multivariate regression weight model. The model permits visualization of the design space and assists in optimization of the drive system preliminary design. This methodology is applied to both the Boeing HLH and the Russian Mi-26 main gearboxes. This study applies the drive system design methodology to compare the Mi-26 split-torque gearbox over the Boeing HLH multi-stage planetary gearbox in a single main rotor heavy lift helicopter.
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Books on the topic "Helicopter transmissions"

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Chaiko, Lev. Assessment of worm gearing for helicopter transmissions. [Washington, DC]: National Aeronautics and Space Administration, 1990.

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Choy, Fred K. Dynamics analysis of multimesh-gear helicopter transmissions. Cleveland, Ohio: Lewis Research Center, 1988.

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Michael, Savage. System life and reliability modeling for helicopter transmissions. Cleveland, Ohio: Lewis Research Center, 1986.

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Savage, M. System life and reliability modeling for helicopter transmissions. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.

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Krantz, Timothy L. Experimental and analytical evaluation of efficiency of helicopter planetary stage. Cleveland, Ohio: Lewis Research Center, 1990.

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Handschuh, Robert F. Experimental testing of prototype face gears for helicopter transmissions. [Washington, DC: National Aeronautics and Space Administration, 1992.

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Lewicki, David G. Vibration characterstics of OH-58A helicopter main rotor transmission. Cleveland, Ohio: Lewis Research Center, 1987.

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Lewicki, David G. Evaluation of an oil-debris monitoring guide for use in helicopter transmissions. [Washington, DC]: National Aeronautics and Space Administration, 1992.

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Lewicki, David G. Evaluation of an oil-debris monitoring guide for use in helicopter transmissions. [Washington, DC]: National Aeronautics and Space Administration, 1992.

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Lewicki, David G. Evaluation of an oil-debris monitoring guide for use in helicopter transmissions. [Washington, DC]: National Aeronautics and Space Administration, 1992.

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Book chapters on the topic "Helicopter transmissions"

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Mariani, Ugo, Rosanna Molinaro, Sergio Sartori, Giuseppe Gasparini, and Carlo Gorla. "Improvements in Fatigue Evaluations of Helicopter Transmissions." In ICAF 2011 Structural Integrity: Influence of Efficiency and Green Imperatives, 959–69. Dordrecht: Springer Netherlands, 2011. http://dx.doi.org/10.1007/978-94-007-1664-3_72.

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Davies, D. P. "Duplex Hardening: An Advanced Surface Engineering Technique for Helicopter Transmissions." In Surface Engineering, 228–37. Dordrecht: Springer Netherlands, 1990. http://dx.doi.org/10.1007/978-94-009-0773-7_24.

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Vershinina, N. V., and M. V. Boiko. "Tribological Diagnostics of the Mi-26 Helicopter Tail Transmission." In Lecture Notes in Mechanical Engineering, 1228–35. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-54814-8_142.

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Chebakov, M. I., S. A. Danilchenko, and E. M. Kolosova. "Simulation of the Stress-Strain State of the Spline Joint of the Helicopter Tail Transmission." In Springer Proceedings in Materials, 405–13. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-45120-2_33.

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Pritzl, Václav, Lukáš Vojtěch, Marek Neruda, and Martin Saska. "Real-Time Localization of Transmission Sources by a Formation of Helicopters Equipped with a Rotating Directional Antenna." In Modelling and Simulation for Autonomous Systems, 335–50. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-14984-0_25.

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Watkinson, John. "Engines and transmissions." In Art of the Helicopter, 191–257. Elsevier, 2004. http://dx.doi.org/10.1016/b978-075065715-0/50007-7.

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"Helicopter Main Rotor Transmission Output Shaft Failure." In ASM Failure Analysis Case Histories: Air and Spacecraft. ASM International, 2019. http://dx.doi.org/10.31399/asm.fach.aero.c9001505.

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Han, B., H. W. Wang, X. H. Yang, and Y. Wang. "An approach to transmission configuration in helicopter preliminary design." In International Gear Conference 2014: 26th–28th August 2014, Lyon, 559–65. Elsevier, 2014. http://dx.doi.org/10.1533/9781782421955.559.

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Yin, Z. Y., D. Mi, L. Z. Zhang, X. X. Cai, and H. M. Wu. "Multidisciplinary and multiobjective design optimization of advanced helicopter power transmission system." In Power Engineering, 485–500. CRC Press, 2016. http://dx.doi.org/10.1201/9781315386829-75.

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"Fatigue Failure of a Carburized Steel Gear From a Helicopter Transmission." In Handbook of Case Histories in Failure Analysis, 228–30. ASM International, 1992. http://dx.doi.org/10.31399/asm.fach.v01.c9001077.

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Conference papers on the topic "Helicopter transmissions"

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Litvin, F. L., J. C. Wang, R. B. Bossler, Y. J. D. Chen, G. Heath, and David G. Lewicki. "Application of Face-Gear Drives in Helicopter Transmissions." In ASME 1992 Design Technical Conferences. American Society of Mechanical Engineers, 1992. http://dx.doi.org/10.1115/detc1992-0033.

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Abstract The use of face gears in helicopter transmissions was explored. A light-weight, split torque transmission design utilizing face gears was described. Face-gear design and geometry were investigated. Topics included tooth generation, limiting inner and outer radii, tooth contact analysis, contact ratio, gear eccentricity, and structural stiffness. Design charts were developed to determine minimum and maximum face-gear inner and outer radii. Analytical study of transmission error showed face-gear drives were relatively insensitive to gear misalignment, but tooth contact was affected by misalignment. A method of localizing bearing contact to compensate for misalignment was explored. The proper choice of shaft support stiffness enabled good load sharing in the split torque transmission design. Face-gear experimental studies were also included and the feasibility of face gears in high-speed, high-load applications such as helicopter transmissions was demonstrated.
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Showalter, Stephen, Sachin Pingalkar, and Sadiq Pasha. "Oil debris monitoring in aerospace engines and helicopter transmissions." In 2012 1st International Symposium on Physics and Technology of Sensors (ISPTS). IEEE, 2012. http://dx.doi.org/10.1109/ispts.2012.6260907.

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Showalter, Stephen, Sachin Pingalkar, and Sadiq Pasha. "Oil debris monitoring in aerospace engines and helicopter transmissions." In 2012 1st International Symposium on Physics and Technology of Sensors (ISPTS). IEEE, 2012. http://dx.doi.org/10.1109/ispts.2012.6260912.

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ASTRIDGE, D. "Advanced techniques for health and usage monitoring of helicopter transmissions." In 21st Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1985. http://dx.doi.org/10.2514/6.1985-1142.

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LEWICKI, DAVID, ROBERT HANDSCHUH, ZACHARY HENRY, and FAYDOR LITVIN. "Low-noise, high-strength, spiral-bevel gears for helicopter transmissions." In 29th Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-2149.

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6

Clerici, Paolo, Ambrogio Girotti, and Alessandro Perazzolo. "Comparison of Web Stress Concentration Factors and Safety Margins for a Thin Webbed Spur Gear Subjected to Static and Cyclic Loading Conditions." In ASME 1992 Design Technical Conferences. American Society of Mechanical Engineers, 1992. http://dx.doi.org/10.1115/detc1992-0007.

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Abstract The stress distribution in the holed web of a gear was studied in order to evaluate the effects of overstress caused by a reduction in weight in comparison with a gear without lightening holes. The analysed gear is a component of a helicopter principal transmission: geometry and dimensions (web with eight circular holes) are usually employed. A 3-D mesh of the gears was made using PATRAN and a FEM analysis was carried out using NASTRAN 65a2. Moreover the principal stress history in one revolution of the gear was reconstructed at the critical points of the web. Thus it was possible to evaluate the actual fatigue cycle and the consequent safety margin for the different load conditions under which helicopter transmissions are generally checked. It was found that the stress variations in one revolution of the gear are significant even in constant power conditions and that the stresses at each point on the border of the holes always have the same sign in a complete revolution. Safety margins in the web were evaluated and compared using different formulas.
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Krantz, Timothy L. "Gear Tooth Stress Measurements of Two Helicopter Planetary Stages." In ASME 1992 Design Technical Conferences. American Society of Mechanical Engineers, 1992. http://dx.doi.org/10.1115/detc1992-0008.

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Abstract Two versions of the planetary reduction stages from U.S. Army OH-58 helicopter main rotor transmissions were tested at the NASA Lewis Research Center. One sequential and one nonsequential planetary were tested. Sun gear and ring gear teeth strains were measured, and stresses were calculated from the strains. The alternating stress at the fillet of both the loaded and unloaded sides of the teeth and at the root of the sun gear teeth are reported. Typical stress variations as the gear tooth moves through the mesh are illustrated. At the tooth root location of the thin-rimmed sun gear, a significant stress was produced by a phenomenon other than the passing of a planet gear. The load variation among the planets was studied. Each planet produced its own distinctive load distribution on the ring and sun gears. The load variation was less for a three-planet, nonsequential design as compared to that of a four-planet, sequential design. The results reported enhance the data base for gear stress levels and provide data for the validation of analytical methods.
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Patrick, Romano, Al Ferri, and George Vachtsevanos. "Detection of Carrier-Plate Cracks Using Vibration Spectra." In ASME 2007 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2007. http://dx.doi.org/10.1115/detc2007-35091.

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This paper examines the problem of identifying cracks in planetary gear systems through use of vibration sensors on the stationary gearbox housing. In particular, the effect of unequal spacing of planet gears relative to the rotating carrier plate on various frequency components in the vibration spectra is studied. The mathematical analysis is validated with experimental data comparing the vibration signature of helicopter transmissions operating either normally or with damage leading to shifts in the planet gear positions. The theory presented is able to explain certain features and trends in the measured vibration signals of healthy and faulty transmissions. The characterization offered may serve as a means of detecting damage in planetary gear systems.
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Coker, Joseph D., Darryll J. Pines, Paul D. Samuel, and Jason Kiddy. "Fiber Optic Strain Sensor Vibration Separation for Detection of Seeded Faults in Rotorcraft Transmissions." In ASME 2008 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. ASMEDC, 2008. http://dx.doi.org/10.1115/smasis2008-432.

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This paper presents a refined methodology for performing helicopter transmission anomaly detection through the use of vibration separation techniques applied to the output of a fiber optic sensor array. Fiber Bragg grating (FBG) sensors—distributed about the exterior of a planetary gearbox annulus—record the local strain response of the annulus surface due to tooth-mesh interactions. These strain profiles are collected for a number of loading conditions both with and without seeded faults. The profiles are separated and synchronously averaged to illustrate the effect of damage to planetary gears on local strain variation. Results of experiments conducted on the University of Maryland Transmission Test Rig (UMTTR) are included. Additional processing and comparison to traditional vibration-based diagnostic methods indicate the potential for increased sensitivity to damage of such a system and the feasibility of fiber optic strain sensors for in situ health and usage monitoring.
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Mosher, Marianne. "Understanding Vibration Spectra of Planetary Gear Systems for Fault Detection." In ASME 2003 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2003. http://dx.doi.org/10.1115/detc2003/ptg-48082.

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This paper explores the vibration spectra for planetary gear systems by studying a kinematic model of vibration and comparing the model with measurements of two helicopter transmissions made in flight. The model and flight data include systems with both uniformly and nonuniformly spaced planet gears. This model predicts vibration to occur only at frequencies that are integer multiples of the planet spacing repetition frequency and clustered around gear mesh harmonics. Vibration measurements show the model correctly predicts the frequencies with large components around the first several harmonics of the gear mesh frequency. Measurements do not confirm some of the more detailed features predicted by the model. Some features in the spectra from the numerically derived model can be used to separate the model data with and without planted faults. These features were not found useful for detecting faults in the vibration measurements of real gearboxes in flight due to added complexity in the spectra from real gearboxes.
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Reports on the topic "Helicopter transmissions"

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Litvin, F. L., J. C. Wang, R. B. Bossler, Chen Jr., Heath Y. J., and G. Application of Face-Gear Drives in Helicopter Transmissions. Fort Belvoir, VA: Defense Technical Information Center, January 1992. http://dx.doi.org/10.21236/ada257727.

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