The node of the planetary gear

IPC classes for russian patent The node of the planetary gear (RU 2145396):

F16H57/08 - of gearings with members having orbital motion

B64C27/14 - Direct drive between power plant and rotor hub

Another patents in same IPC classes:

Transfer / 2126918

The invention relates to a transmission, in particular to the planetary transmission with the main body, with at least one output element mounted for rotation, and with the annular socket with work surfaces made in the area of the output item for the same cylinder of the rolling elements

Drive / 2094677

The invention relates to machine tools and can be used in the composition of the products of aviation and rocketry

Planetary gear / 2037695

Helicopter gearbox / 2250180

Proposed gearbox of helicopter main rotor includes two drive gears and one driven gear mounted on shaft of main rotor drive. Engines are mounted for rotation towards each other. Driven gear of main rotor shaft is directly connected with one drive gear; it is connected with other drive gear through idler.

Coaxial helicopter reduction gearbox / 2309874

Proposed reduction gearbox for coaxial helicopter includes drive shaft, two coaxial driven shafts (inner and outer), gear train and planetary mechanisms which are kinematically interconnected; each mechanism includes sun gear wheel fitted on drive shaft and epicycle fitted on outer driven shaft. Gear train mechanism has idler units placed in carrier which is rigidly secured on inner driven shaft; number of satellites exceeds number of idler units by one; number of teeth of sun gear wheel and epicycle of gear train mechanism is multiple of number of idler units; total number of teeth of these members in planetary mechanism is multiple of number of satellites.

Multi-flow reducer for rotorcraft / 2402710

System of reducer consists of multitude of three-step modules (26A, 26B, 26C) of power tooth gear dividing flow of torque; each module transmits torque from high-speed engine to shaft (24) of lifting screw. A packaged design of a conic flat tooth gear of the first step (S1) facilitates installation of the engine in various positions along all axes. On the second step (S2) units of hollow shafts ensure equal balance of load. On the third step (S3) each unit of the hollow shaft includes multitude of small gears engaging an output tooth gear (28) of the last step.

Helicopter reduction gearbox / 2541566

Invention relates to aviation, specifically to helicopter transmission designs. Helicopter reduction gearbox includes case where following parts are located: bevel gear wheels connected with shafts of helicopter rotors, bevel gear forming engagements with mentioned bevel gear wheels of rotor shafts and connected with shaft mounted on tapered rolling bearings and with gear wheel fitted on this shaft. Inner rings of tapered bearings are fixed in axial direction relative to shaft, and outer rings are installed with thrust against case and sleeve beads in "tensioned" pattern. Outer bearing ring installed adjacent to crown of bevel gear has possibility of hard contact with case bead, and outer ring of the other bearing has possibility to rest on inner bead of sleeve. The latter is located in case hole with groove to interact with key connected with surface of the mentioned sleeve. Sleeve surface extends from case by its outside thread. Nut end can contact with reduction gear case from outside. The nut is made as closed cup with grooves in one of which tooth of locking device is placed. The locking device is attached to helicopter reduction gearbox case.

Coaxial-rotor helicopter gearbox / 2541569

This gearbox comprises housing to accommodate spinning hollow vertical and coaxial shafts. Rotor is fitted on one end of every said shaft. Sump is arranged in housing case and coupled via bearings and tapered gearing with second ends of hollow shafts of upper and lower rotors. Note here that vaned pump wheel is fitted on upper rotor shaft its vanes being arranged at angle α relative to its radius and provided with orifices arranged regularly on its lower end surface, axes of said orifices being parallel with pump wheel axis. Vanes on sump inner surface are arranged at angle α relative to its radius directed opposite inclination of the vanes of said pump wheel. Chamber case is filled with lubricant and communicated via channel, clearances and orifices with bearings and gearings.

Planet gear / 2291335

Planet gear comprises solar pinion (1), satellites each of which is composed of two wheels (2), unmovable wheel (8) with inner teeth, and carrier (7). Wheels (2) of the satellites are mounted on the axle (3) in spherical bearings (4). The unit of each satellite is provided with rubber ring (5) having variable cross-section area. Rubber ring (5) bears on centering washer (6) and interposed between wheels (2) of the satellite. Carrier (7) is provided with openings made in the webs in a staggered order. The diameter of the openings increases with the distance from the axle of the satellite.

Carrier for planetary reduction gear / 2294470

Proposed carrier has drive shaft, right-hand and left-hand cheeks, central plate arranged between cheeks, main axle secured in coaxial holes of cheeks and central plate. Planet pinions for two planetary gear trains are installed on main axle on bearings. Right-hand cheek is rigidly connected with central plate. Left-hand cheek is coupled with central plate by bridges. Central plate is connected with drive shaft. Intermediate axle is installed in coaxial holes of cheeks and central plate. Planet pinion of one planetary gear train is arranged on main axle on section between left-hand cheek and central plate. Planet pinion of other planetary gear train is arranged on main axle on section between right-hand cheek and central plate, being engaged with planet pinion installed on intermediate axle on the same section.

Method for increasing rigidity of planetary gear carrier / 2303729

Method for increasing rigidity of planetary gear carrier is realized by creation of directional preliminary voltage by means of eccentric bushings (4) in cross connection fingers (3), connecting flanges (1,2) of carrier in single unit.

Gear ratio converter / 2304735

Gear ratio converter comprises planet differential provided with the driving carrier and central gear wheels of different diameters. One of the gear wheels is secured to the output shaft for permitting power transmission to the output shaft. The second gear wheel loads the friction device with a given sliding force. The driven part of the friction device is rigidly connected with the third central gear wheel that freely rotates on the output shaft and transmits rotation to the fourth central gear wheel through the reduction gear. The fourth central gear wheel is rigidly connected with the output shaft.

Planetary gearbox central support member / 2313020

Proposed central support member has housing 26 installed in gearbox case and made in form of ring. Ring groove 28 made on one side of ring serves to support plate spring. Aligning blind hole 29 serves for fitting adjacent part. Two ring concentric spaces 30, 31 of smaller and larger diameter are made on other side of ring. Surface of wall in concentric space 30 near longitudinal axis of housing is smooth, and surface at a distance from longitudinal axis of housing is made stepped. Surface of first step of smaller diameter is smooth. Surface of other step is provided with splines and channels for lockrings. Surface of smaller diameter wall in concentric space 31 is smooth, and on surface of all of larger diameter splines are made. Ring is provided with tetragonal through holes 38 equally spaced over circumference, conical in direction of groove 28. Oil feed channel 27 in side surface 37 of ring communicates with concentric space 30.

Gearbox / 2319623

Gearbox is designed for mounting onto all-wheel-drive trucks. Gearbox case 1 accommodates drive shaft 2, countershaft 3, driven shaft 4, reverse idler gear 5, planetary gear train 6 and interaxle differential 7 are installed on one axle and have common carrier 8. Sun gear of planetary gear train 10 is installed on driven shaft 4. Fitted on drive shaft 2 are double-acting clutches 11 and 12, four rotating gears 13, 14, 15 and 16 and two fixed gears 17 and 18. Fitted on countershaft 3 are double-acting clutch 19, two rotating gears 20 and 21, and four gears 22, 23, 24 and 25 which are fixed. Double-acting clutch 26 and two rotating gears 27 and 28 are installed on shaft 3. Planet pinions 29 of planetary gear train and planet pinions 30 of interaxle differential are arranged on one axle. Ring gear 9 of planetary gear train can alternately engage with toothed rim 31 secured on case 1 and toothed rim 32 on carrier 8. Ring gear 33 of planetary mechanism of interaxle differential is in constant meshing with toothed rim 34 which is secured on shaft 35 of axle drive and can be meshed with toothed rim 36 secured on carrier 8. Sun gear of planetary mechanism of interaxle differential is installed on axle drive shaft 38.

Rpm gearbox with flexible joint between satellite race and fixed bracket / 2332598

Invention relates to rpm gearbox designed, in particular, to transmit torque between the gas turbine and compressor in the gas turbine engine. The gearbox comprises planetary gear (2), crown wheel (3) and satellites (4) arranged in separator (8) furnished with axial well (11) between two adjacent satellites. Separator (8) is connected to separator bracket (12) incorporating axial posts (14) fitted in sockets (11) by means of radial pins (15) arranged in the medium plane of separator (8) and coupling (20) enclosing pin (15) and containing two circular end face flanges and several axial sleeves arranged between them to ensure inclination and axial shift of separator bracket (12) relative to separator (8). One of the sleeves is made from elastomer.

Planetary gear and drive unit comprising such gear / 2358171

Planetary gear comprises carrier having driver chucks (21, 22) of the first and second side, links (23) and end part (15a). The second convex part (22a) of front driver chuck (22) is arranged so that its width in peripheral direction is more than the width of the first convex part (21a) of back driver chuck (21). The second convex part (22a) may be welded to annular gear wheel (25) at connection part (38) from the side of XI direction in axial direction. Therefore, it is possible to weld back driver chuck (21) to link (23) of carrier, and also external edge (22c) of front driver chuck (22) - to annular gear wheel (25) from the same direction, and to eliminate operation of carrier and input shaft (15) turnover.

Supporting device / 2401953

Support device consists of case (4) wherein there is mounted hollow shaft (1). At least two rolling bearings with separators (6), with external (3) and internal (2) rings and rolling bodies (5) are installed at an interval on the hollow shaft. Support (7) of separators (6) is made in form of a hollow pipe and is positioned inside shaft (1) coaxially to the shaft and cylinder rod (8), secured on case (4) and equipped with channels (9) for supply of oil.

Attachment point of crown gear in planetary or differential reducer / 2402711

Attachment point of crown gear in planetary of differential reducer consists of crown gear (1) coupled with hub (2) of crown gear by means of tooth coupling. Height of teeth of crown gear (1) is equal to height of teeth of hub (2). Groove (3) is made in rim of crown gear (1) wherein there is installed spring ring (4), while a slot is made on end surface of crown gear (1). Spring ring (4) is split; its ends are bent upward and enter the slot of crown gear (1). Circular groove (7) is cut in the rim of hub (2).

(57) Abstract:

The invention relates to the nodes of the planetary gear, in particular to the nodes of the planetary gear with multi-level stepped arrangement of satellites for transmission of the helicopter. The node of the planetary gear with multi-level stepped arrangement of satellites consists of leading Central gears, a set of N primary satellites, set the secondary satellites, satellite shaft that has one primary and the secondary satellite, a stationary annular gears and satellitedata. The specified satelliteoperating installed on the aggregate of the upper and lower aggregate bearings to rotate simultaneously with the rotation of the satellite shafts and transmit torque to the shaft of the main rotor of the helicopter. Set primary satellites is divided into a set of N/2 upper primary satellites and a set of N/2 lower primary satellites. The upper and lower primary satellites are located on two levels of speed, in alternate order, in which each upper primary satellite overlaps with the profiles directly coterminous with the bottom pervious output power of the power plant while maintaining the original number of revolutions of the shaft of the main rotor. 2 C.p. f-crystals, 8 ill., table 1.

The technical field to which the invention relates
The present invention relates to the nodes of the planetary gear and, in particular, to the nodes of the planetary gear with multi-level stepped arrangement of satellites for improved transmission of the helicopter, and this node planetary gear system with multi-level stepped arrangement of satellites has two primary satellites, arranged in alternating order, which accounts for the increased gear ratio, compensating for the increased output power and the improved propulsion while maintaining the original number of revolutions of the shaft of the main rotor.

Art
Manufacturers of helicopters continuously expand the range of applicable technologies, enabling them to offer customers the most advanced helicopters at an affordable price. Due to the enormous costs associated with the extension to market the aircraft of the new helicopter, which embodies the latest achievements of technology, the promotion of this helicopter this particular manufacturer has become relatively unique event. The cycle of creating a new helicopter from the exploratory stage also does not contribute to the frequent appearance of new types of helicopters.

Alternatively, new helicopters, many manufacturers of helicopters offer the modernization of basic production models, in other words - modified variants of helicopters. Such modified variants, resulting from selective introduction of advanced technologies in the production of the base case may have new or enhanced capabilities, improved performance, higher reliability and/or operational adaptability. By keeping most elements of the design base case, the cost of development and production, as a rule, not much higher than the cost of development and production of the base case. Moreover, the cycle of development and production of a modified version may be relatively inconsistent, as the production of modified variants can be implemented on the production lines for the base variant, in parallel with it, or alternatively in the form of modernization of basic production version.

Mentioned an alternative approach to modernization, more importantly, can bring additional benefits to the manufacturer of helicopters. Selective introduction into the process of sør the option, can serve as a basis for improvement of existing basic serial variants of the helicopter. Refine the basic serial variants of the helicopter, in addition to economic benefits for the manufacturer of helicopters, gives the customer the ability to convert basic serial option (options) of the helicopter in its more perfect modified version.

One of the most popular approaches to modernization of the basic option is to install a more powerful power plant. The increased power of such a power plant can significantly improve the performance characteristics of the modified options and to expand the range of tasks. Moreover, an improved power unit provides the Foundation for application on a modified version further promising technical solutions. For example, for advanced propulsion may be provided by an additional auxiliary power supply modules of the helicopter.

However, the setting on the base serial variant of the helicopter advanced propulsion systems may require significant design modifications of the basic transmission under great is their gear ratio (gear ratio) of the transmission in order to bring it in line with the increased torque value, develop power plant, the change of structural elements connecting the power unit with the airframe of the helicopter, moving the attachment points of the intake and the hinged mounting of the engines, the transfer actuator units, the transfer of the steering screw, expansion compartment of the main gearbox, i.e. the increase of its diameter and/or height, caused by structural changes in the transmission, which may require the transfer of the attachment points of the main gearbox, i.e., the struts to the fuselage. Structural and functional conversion of basic production version of the helicopter, and in particular its transmission, representing one of the approaches to the modernization of the helicopter due to the installation of more powerful power plant, requires the investment of considerable resources in upgrading the helicopter and restrains the beginning of the extension of the modified version on the markets.

Moreover, in practice, this approach to the revision of the helicopter excludes upgrades, better power plant on production instances of the base variant of the helicopter. If the financial costs and time spent on the production of the first modified versions of the helicopter and selling them can be Adullam costs and time spent on the modernization of basic production version of the helicopter can be added for additional costs from organizations, operating the base variant of the helicopter, expressed in the form of lost profits due to a forced outage of the helicopters, which will be finalized.

U.S. patent N 3,540,311 describes variant become automatically self-centering of the planetary gear system comprising a host Central gear (218), the first set of planetary elements (222a, 222b) containing the axis (224) having a rolling surface (228), the set of satellites (220a, 220b), which is in mesh with the Central gear (218), and second satellites (226) in the internal meshing with a fixed gear wheel (230) and the second set is a compound planetary elements (232) containing hollow axis (234), which includes satellites (236) in the internal meshing with the output gear wheels (240), seated on the output shaft (244), and satellites (238) in the internal meshing with a fixed gear wheel (242). The rolling surface (228) each axis (224) mechanical contact with the inner surface of the respective hollow axis (234), resulting in the load axis (224) is transmitted on a corresponding hollow shaft (234). Satellites (220a, 220b) are located in this alternating on S="ptx2">

Samoustraniajutsia planetary gear train disclosed in U.S. patent N 3,540,311, does not use in its design bearings limiting radial displacement and distortion of the transmission elements. Instead, through mathematical calculations, the axial spacing between the elements of each axis (224, 234) are selected so that the resulting moment causing the misalignment of the axes (224, 234), is approximately equal to zero. For each axis 224 of the axial gap between the second satellite (226), the surface of the roller 228 and the satellite (220a) or in another case between the second satellite (226), the surface of the roller 228 and the satellite (220b) is of such a magnitude that the force, resulting in a rotation of the satellite (220a) or in another case, the satellite (220b), the reaction force acting on the toothed wheel (226), and the power output, the current in the center of the rolling surface (228), are collinear F. Similarly, for each hollow axis (234) the axial gap between the satellite (236), satellite (238) and the rolling surface (228) such that the point of application of the input force acting from the side of the rolling surface (228) on the hollow shaft (234), the point of application of force output to the satellite (236) and the point of application of reaction forces to the satellite (238) are on a straight line G.

Plodnosti, develop power plant (80, 180), and contains the first gear stage (22, 32, 34). The transmission also includes a main gearbox containing the second gear stage (60, 62) is mechanically connected to the first gear stage (22, 32, 34) and perceiving from the output of the power plant, drive shaft (64) and the third gear stage, which consists of the Central gear wheel (66), satellites (70), the stationary annular gear (72) and ring satelliteoperating (74). The Central gear wheel (66) planted on the drive shaft (64), and the torque is removed from the third gear stage, is passed through the annular satelliteoperating (74) on the rotor shaft (76) of the helicopter.

It is necessary to develop an improved transmission having sufficient similarity with the transmission of the base variant of the helicopter, to enable improvements improved powertrain under the base variant of the helicopter, equipped with a more powerful power plant or finalizing the installation. This improved transmission shall, to the maximum extent have the similarity with the existing transmission base variant of the helicopter that passco basic variant of the helicopter for the purpose of their conversion to modified versions in a short period of time with acceptable cost. Improved transmission must contain a node of the planetary gear with multi-level stepped arrangement of satellites, which has two primary satellites, arranged in alternating order, thereby increasing the gear ratio, compensating for the increased output power and the improved propulsion while maintaining the original number of revolutions of the shaft of the main rotor.

The invention
The objective of the invention is to provide an improved transmission of the helicopter, with the possibility of improvements to the basic serial version of the helicopter, equipped with advanced propulsion or finalizing the installation.

Another objective of the present invention is to create a node of the planetary gear with multi-level stepped arrangement of satellites, with two primary satellites, arranged in alternating order, thereby increasing the gear ratio, compensating for the increased output power and the improved propulsion while maintaining the original number of revolutions of the shaft of the main rotor.

The next task of the present invention solucionario stepped arrangement of satellites, it has two primary satellites, arranged in alternating order, with sufficient similarity to the transmission of the base variant of the helicopter to enable improvements improved powertrain under the base variant of the helicopter, equipped with a more powerful power plant or finalizing the installation.

The next task of the present invention is to create a planetary gearbox with multi-level stepped arrangement of satellites for the initial transmission, fit into this original transmission structurally, functionally and with the preservation of its geometrical parameters, including the installation of the radial dimensions of the housing, the location of the point of engagement of the main bevel gear vertical and the height of the ceiling of a cabin of pilots.

These and other problems are solved by a node of the planetary gear with multi-level stepped arrangement of satellites in accordance with the present invention and which is the third step of the improved gear system with a high gear ratio that compensates for increased power output advanced power Evoy stepped arrangement of satellites consists of leading Central gear, the set of N primary satellites, set the secondary satellites, satellite shaft that has one primary and the secondary satellite, fixed annular gear wheel which engages with the secondary satellites, as well as satellitedata, having the ability to rotate simultaneously with the rotation of the satellite shafts and intended for transmitting torque from a node of the planetary gear on the driven mechanism. The set of N primary satellites is divided into a set of N/2 upper primary satellites and a set of N/2 lower primary satellites. The upper and lower primary satellites are located on two levels of speed, in alternate order, in which each upper primary satellite overlaps with the profiles directly coterminous with the bottom of the primary satellites. The node of the planetary gear with multi-level stepped arrangement of the satellites has a combination of upper and lower bearings, which together serve as a support node satellitedata, allowing it to rotate together with the satellite shafts.

Next, the node of the planetary gear with multilevel step componentcollection first given diameter, installed on the bottom of the primary satellites and satellite shafts having a support part of the second given diameter, is installed on top of the primary satellites. The value of the second predetermined diameter is selected so as to provide minimum clearance between the support area of the satellite shaft, is installed on top of the primary satellite, overlapping profiles directly coterminous with the lower primary satellites, and the toothed crowns of the lower primary satellites.

The node of the planetary gear with multi-level stepped arrangement of satellites, made according to the present invention, operates as a third stage of an improved gear system, having an input receiving the output power and the improved propulsion. Input modules contain the first gear stage, the transmission power on the main gear. The second gear stage, part of the main gearbox that transmits power to the node of the planetary gear with multi-level stepped arrangement of satellites rotating the Central gear wheel.

Brief description of drawings
the years, described with reference to the accompanying drawings:
Fig. 1 - axonometric image of an improved transmission of the helicopter, including the node of the planetary gear with multi-level stepped arrangement of satellites, made according to the present invention;
Fig. 1A - axonometric image base powertrain production version of the helicopter UH-60;
Fig.2A - node of the planetary gear system in schematic representation;
Fig. 2B is a system with a fixed centre, the equivalent node of the planetary gear transmission according to Fig.2A, a schematic image;
Fig.3 is a cross section of the node of the planetary gear with multi-level stepped arrangement of satellites, made according to the present invention;
Fig. 4 is a top view of the fragment node planetary gear system with multi-level stepped arrangement of the satellites in Fig.2, showing a multi-level layout of the primary satellites with overlapping profiles included in a node of the planetary gear with multi-level stepped arrangement of the satellites in Fig.3:
Fig. 5 is a side view of a fragment of the node of the planetary gear with multilevel step Kearney gear with multi-level stepped arrangement of satellites, demonstrating its features in accordance with the present invention.

Information confirming the possibility of carrying out the invention
Refer to the drawings, in which identical or similar elements are marked unified numbering positions. In Fig.1 shows a typical variant of the improved transmission 100 of the helicopter containing the node of the planetary gear 10 with multi-level stepped arrangement of satellites, made according to the present invention. Improvement of the transmission 100 is in ensuring its structural and functional compatibility with a more powerful power plant and, at the same time, structural similarities with the basic transmission existing serial variants of the helicopter. Described below improved transmission 100 is designed for use on serial versions of helicopters, power plant which contains two removable motor module that allows you to quickly modernize these serial samples of the helicopter by installing a more powerful engine modules or modifications of the engines increased power.

Removable motor modules installed on each side glavnog who ate of the output shaft, the mountings of the engine, exhaust pipe, pipelines, fuel and oil systems and wiring. The main function of advanced powertrain 100 is to transmit the total power developed advanced motors 102A, 102B (for simplicity, they are marked in Fig. 1 "building blocks") on the main gear 104, the rotor shaft 106, a sub-steering screw 108. Advanced task advanced powertrain 100 is the removal of power to drive the electric and hydraulic units.

Although their structural and functional characteristics of the node of the planetary gear 10 with multi-level stepped arrangement of the satellites is characterized as an integral part of advanced powertrain 100 helicopter, for professionals it should be clear that the description of such variants do not limit the scope of patent protection of the invention. The node of the planetary gear 10 with multi-level stepped arrangement of satellites, made according to the present invention and having a set of essential features set forth in the attached formula, can be embodied in the form of technical decisions, other than those addressed by the plans advanced propulsion modules 102A, 102B, and the main module 126. Each input module 110A, 110B connected to the corresponding motor module high power 102A, 102B through a node of the output shaft of the engine 112A, 112B, thereby included in the transmission path of the power from this engine, and contains the first gear stage 114A, 114B (consisting, as shown in the drawing, of the drive and driven bevel gears, freewheel 116A, 116B, and an output shaft 118A, 118B with firmly planted on his gears. In addition, each input module 110A, 110B equipped drive unit corresponding hydraulic pump 122A, 122B and generators 124A, 124B.

In the main module 126 includes a second gear step 128 (Fig. 1 only visible to the second gear stage 128A, because the leading wheel of the second gear stage 128B covered shaft rotor 106), the drive shaft 130 and the node of the planetary gear 10 with multi-level stepped arrangement of satellites, made according to the present invention, which plays the role of the third gear stage advanced powertrain 100. The second gear stage 128 is composed of leading bevel gears in tracts A and B transmit power from the engines, and the bevel gear wheel, in turn, transmits power through the drive shaft 130 to the node of the planetary gear 10 with multi-level stepped arrangement of satellites, made according to the present invention. The main module also has a drive unit 132 units and drive unit 134 of the transmission of the steering screw 108, which includes a primary tail shaft 136, passing in the tail boom, intermediate gear 138, the secondary tail shaft 140, held in end beam, tail gear 142 and the shaft tail rotor hub 144, transmitting power to the steering bushing screw with the attached blades (not shown in the drawing), compensating the reactive torque of the main rotor.

In Fig. 1A presents the base case transmission 100' BLACK HAWK helicoptersand SEAHAWKmanufactured by Sikorsky aircraft (BLACK HAWK and SEAHAWK are registered trademarks of Sikorsky aircraft Dilijan of United technologies Koperasi).

Transmission 100' in base version in General is structurally and functionally similar to the advanced powertrain 100, described in the previous paragraphs, with the exception of the third gear stage. In the basic variant is CNY node of the planetary gear 150 is composed of a Central slave gears 152 (transmitting power from the drive shaft 130 to the node of the planetary gear 150), a stationary annular gears 154 and node satellitedata 156 that has multiple satellites 158, rotating around its axis and simultaneously around the Central slave gears 152. Node satellitedata 156 transmits power from the third gear stage on the rotor shaft 106, while maintaining its base speed.

The above improved transmission 100, containing a node of the planetary gear 10 with multi-level stepped arrangement of satellites, made according to the present invention, designed for use by helicopter S-92^TMHELIBUS^TMdeveloped by the company Sikorsky aircraft S-92 HELIBUS are trademarks of Sikorsky aircraft Dilijan of United technologies Koperasi). Structural and functional appearance of the node of the planetary gear 10 with multi-level stepped arrangement of satellites, part of the advanced powertrain 100, was determined mainly by two design tasks. The first task was to enable the installation of an improved powertrain 100 on serial options helicopters UH-60, manufactured by F. the plan. In other words, the first requirement of the design objectives was to ensure the greatest possible similarity develop transmission basic transmission 100' serial helicopters BLACK HAWKand SEAHAWK.

The need for this requirement imposed some design constraints on the improved transmission 100. Among other restrictions have been put forward requirements: preserve the dimensions of the main gear transmission 100 helicopter S-92^TMat the level of values for the main gearbox of the helicopter BLACK HAWK^TMand SEAHAWK(in particular, equal radial dimensions to ensure interchangeability of struts mounting housing of the main gearbox, while the height is not as critical in this respect, therefore, the increase, if necessary, the height of the main gearbox of the helicopter S-92^TMis valid), the identity of the attachment points of the intake and the hinged mounting of the engines, the identity of the location of the node drive systems, steering screw, and identity level of the water line in a floating state, which does not allow penetration of water is Anna transmission 100 with the power plant increased power. Each of the motors 102A, 102B helicopter S-92^TMHELIBUS^TMdevelops power at the output shaft 1.554.785 W, thus the total capacity of the power plant is 3.169.569 watts. For comparison, the capacity of each engine serial version of the SEAHAWK helicopteris 1.267.690 watts, and the total capacity of the power plant of the helicopter SEAHAWKis 4.535.380 watts. Because of the power loss on the steering screw 134, block units 120A, 120B, hydraulic unit 132, and power loss on friction and others , the power that is perceived by a node of the planetary gear 10 with multi-level stepped arrangement of satellites decreases from the initial value (the output shafts of the motors) 3.169.569 W to values 2.796.375 watts. For comparison, the power perceived by a simple node of the planetary gears of the basic transmission SEAHAWK helicopteris at the level of 2.281.842 watts. Improved transmission 100 and, in particular, the node of the planetary gear 10 with multi-level stepped arrangement of satellites in accordance with the present invention, structurally optimized to effectively transfer the power developed advanced Dorohov shaft rotor 106 is equal to the number of revolutions of the rotor shaft in the base of the transmission 100'. Through design optimization of advanced powertrain 100, aimed at solving the above design objectives and compliance with specified limitations described improved transmission 100, containing a node of the planetary gear 10 with multi-level stepped arrangement of satellites, made according to the present invention, can be installed on serial variants of the BLACK HAWK helicoptersand SEAHAWKmodernized for the installation of improved engines of increased power.

To compensate for the increased power of the motor modules 102A, 102B and the gear ratio of each input module 110A, 110B, i.e., the first gear stage 114A, 114B advanced powertrain 100, is reduced compared to the ratio of the input modules serial version of the SEAHAWK helicopter(81/29 against 80/22). Thus the power transmitted by each of the input modules 110A, 110B and equal 1.554.785 W, comparable to the power transmitted by the input modules SEAHAWK helicopterequal 1.267.690 watts. The rotation frequency at the output of each of the input modules 110A, 110B advanced powertrain 100 is approximately 7483 about/things screw 106 advanced powertrain 100 is set to about 257 rpm (based on the requirement to ensure functional similarities with the basic transmission 100' SEAHAWK helicopter(R). The gear ratio of the second gear stage 128 of the transmission 100 and the second gear stage base transmission 100' SEAHAWK helicopterequal, since the load acting on these stages, also the same. Therefore, to compensate for the reduction gear ratio of the input modules 110A, 110B advanced powertrain 100 it is necessary to increase the gear ratio of the third gear stage of the main module 126 advanced powertrain 100. For the considered example in this variant description transmission need is the gear ratio of the third gear stage of the main module 126 is about 6,27:1 (against values 4,68: 1 gear ratio for simple node of the planetary gears in the basic transmission SEAHAWK helicopter).

As noted above, the third gear stage base transmission 100' BLACK HAWK helicoptersand SEAHAWKis a simple node of the planetary gear 150. On the constructive layout of the third gear stage advanced powertrain 100 in addition to the structural constraints mentioned earlier, imposed design constraints, about, iameter stationary annular gear of the third gear stage advanced powertrain 100 should not exceed the diameter of the stationary annular gear wheel 154 simple node of the planetary gear 150 base transmission 100' BLACK HAWK helicoptersand SEAHAWK. For this option, the diameter of the annular gear wheel must not exceed the value 65,385 see below, the diameter of the Central toothed wheel advanced powertrain 100 should be not less than the diameter of the Central toothed wheel 152 common node of the planetary gear 150 base transmission 100' BLACK HAWK helicoptersand SEAHAWK. For this option, the diameter of the Central toothed wheel must be at least 17,780 see a Possible increase in the height of the main gear box associated with the construction of the third gear stage is acceptable, though not preferred. In any case, the bottom of the main gear may not be in the compartment of the cab.

Engineering studies stage common node of the planetary gear system described above and depicted in Fig.1A, showed that a simple node D. the increased power 2.796.375 W, develop advanced propulsion modules 102A, 102B. For this reason, we studied the possibility of the incarnation of the third gear stage of an improved transmission 100 in the form of the two nodes of the planetary gear.

For the two-node of the planetary gear, a decreasing momentum about 6,27 times, the gear ratio of each stage was limited to a value of about 2.5:1 on bearing life. Resource bearings basic main gearbox serial options SEAHAWK helicopterapproximately 3490 hours. As a result of calculations of resource bearings for the two steps of the analytical model of the two-node of the planetary gears were obtained approximate values, respectively, 710 and 640 hours. When comparing the above values of the resource it is obvious decline at least five times. Naturally, this reduction of bearing life would be unacceptable for a modified version of the transmission. As we studied the bearings of the greatest diameter, which naturally follows from the nature of the imposed structural constraints discussed above (the dominant limitation on ye structural scheme of the third gear stage advanced powertrain 100.

Multi-level nodes of the planetary gear are single-stage node of the planetary gear, characterized by the presence of two satellites in the node satellitedata. In multi-node of the planetary gear system may include one, two or none of the Central gears, one, two, or a single annular gears. In n-tier nodes of the planetary gear depending on the layout of the component parts of the node, i.e. the choice of leading and driven gears, a large variety of variants with different gear ratios. In the evaluation of various configurations of multi-level nodes of the planetary gear as an alternative to the two-node of the planetary gears were asked the following two constraints: the total gear ratio should be approximately 6,27:1 and the direction of rotation of the output element of the system must match the direction of rotation of its input element.

After researching various configurations of multi-level nodes of the planetary gear for numerical evaluation of the achievable values of the gear ratio of the system was chosen as one compone the gears (as opposed to dual Central gears for the two-stage planetary gear), a single annular gears (unlike double annular gears for the two-stage planetary gear), single node satellitedata (unlike dual node satellitedata for two-stage planetary gear) and twenty-four satellites (as opposed to twenty-three satellites for two-stage planetary gear). In Fig.2A and 2B shows the layout of multi-level node of the planetary gears, which were conducted estimates. In this arrangement, the Central gear S1 is leading with respect to the primary satellite P1, through the ring gear R2, the torque is transmitted to the secondary satellite P2, the final link in the system chain power transmission is the node satellitedata (SOA). Each primary satellite P1 and the corresponding secondary satellite P2 mounted on a common shaft DS.

For multi-node of the planetary gear transmission shown in Fig.2A and 2B, the gear ratio is displayed as follows.

The equation of the speed of satellites P1 and P2 driven by a Central gear S1 and the ring gear R2 of the stomach is the transmission number RR, obtain
< / BR>
Multiplying each side of equation (2) on P1/S1 and adding 1, we get
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If the ratio of the diameter of the Central toothed wheel D_sto the diameter of the primary satellite D_pto mean "Ratio", then the geometry of the investigated composition can be roughly linked to the number of satellites (no.pin) in it, setting a condition such placement of satellites, in which neighboring satellites almost touch each other (in practice, spaced at a minimum distance from each other)
< / BR>
Values relationship of diameter D_sCentral gears and the diameter D_pthe primary satellite for a different number of satellites in the planetary transmission, obtained using equation (4) shown in the table.

The analysis of the table shows that with the increase in the number of primary satellites values the relationship D_s/D_pincrease. Values the relationship D_s/D_pwith the increasing number of primary satellites, on the contrary, decreases. Thus, if in multi-node of the planetary gears, it is desirable to have many of the primary satellites (to reduce the weight of transmission and increase the level permissible load), the impact of node pairs of the planetary gear is used 12 primary satellites, the ratio of D_s/D_pwill be approximately equal to 0.31 in. In order to assess the dimensions of the ring gear R2 and the secondary satellite in multi-node of the planetary gear with the twelve primary satellites, the total gear ratio RR equal 6,27, we will substitute the values RR=6,27 and P1/S1=0.31 in equation (4), from which we define the parameter R2/P2. Under given conditions, the ratio R2/P2 is approximately equal 17,0.

The required value of the ratio R2/P2 is approximately equal 17,0, too large for the actual layout of multi-level node of the planetary gear, as in this case, the secondary satellites were too small, and the voltage from the loads are too high. Moreover, the width of the ring gear F (see for example Fig. 2A) for the secondary satellites P2 becomes very large relative to the required diameter of the secondary satellite P2, while the ratio of the width of the ring gear to the diameter of the secondary satellite P2 exceeds the value of 5. The specialist knows that the value of the ratio of the width of the ring gear to the diameter of the gear (F/D) usually does not exceed 1.0, it allows to minimize the negative effects of misalignment of the axes of the gear wheels, which is manifested in the cases when C is on about the conventional multi-level node of the planetary gears in the layout with gear ratio RR equal 6,27:1, with twelve primary satellites practically not realizable with the above structural limitations. A simple analysis shows that the conventional multi-level node of the planetary gear transmission arrangement having a gear ratio RR equal 6,27: 1, and ten primary satellites, cannot be realized in practice with the above structural limitations.

To effectively address the above-mentioned design tasks within the given structural constraints the author of an invention developed node of the planetary gear 10 with multi-level stepped arrangement of the satellites in the General form shown in Fig.1 and more fully disclosed in Fig. 3 to 6. The node of the planetary gear 10 with multi-level stepped arrangement of satellites in accordance with the present invention is structurally and functionally designed as the third gear stage advanced powertrain 100. The node of the planetary gear system 10 ensures that the gear ratio (in the present embodiment of the invention, its value is Sovershenstvovanie motor modules 102A, 102B, thereby maintaining the original basic number of revolutions of the rotor. The node of the planetary gear 10 with multi-level stepped arrangement of satellites, made according to the present invention fits into the design limitations specified above.

As can be seen in Fig.3, the node of the planetary gear 10 with multi-level stepped arrangement of satellites, made according to the present invention, consists of a leading Central toothed wheel 12, the set of N primary satellites 14, consisting in mesh with the Central gear wheel 12, where N is the total number of primary satellites 14 in the system of toothed wheels 10, a set of N secondary satellites 16, satellite shafts 18, which has one primary 14 and secondary 16 satellite, fixed (i.e., rigidly connected with the housing of the main gear) ring-shaped gears 20 and node satellitedata 22, common to all satellites. As shown in Fig.3, the secondary satellites 16 are in engagement with the stationary annular gear wheel 20, and the node satellitedata 22 is installed on the upper and lower bearings 24, 26 for rotation with simultaneous rotation satillieu stepped arrangement of the satellites on the shaft of the main rotor 106, i.e., increased torque at base speed.

The idea staggered layout satellites involves the choice of such values the relationship S1/P1, in which the primary satellites 14 from the set N are located on two levels in a stepped or staggered. One condition of the intent of the stepped arrangement of the satellites is the parity of the number N defines the number of primary satellites 14 in the set. It is necessary for a uniform two-tier stepwise allocation of primary satellites 14. In accordance with this plan the set of N primary satellites 14 node of the planetary gear 10 with multi-level stepped arrangement of the satellites is divided into a set of N/2 upper primary satellites 14U and a set of N/2 "lower" primary satellites 14L, as shown in Fig.4 - 6. Upper primary satellites 14U define the first plane of rotation 30, and the lower primary satellites 14L define a second plane of rotation 32 (see Fig.5). The analysis of Fig. 4 to 6 shows that the upper and lower primary satellites 14U, 14L are uniformly distributed in their respective planes of rotation 30, 32, each of the upper primary satellite 14U symmetric image overlaps the profiles directly lay down the ETP of the ring gear D_p(depending on the ratio S1/P1). The diameter D_U(see Fig.4 and 5) supporting area of the satellite shaft 18, is installed on top of the primary satellite 14U, is a crucial dimension from the point of view of the intent of the stepped arrangement of the satellites. The diameter D_Uthe reference section of the satellite shaft is selected so that the ring gear adjacent the bottom of the primary satellites 14L having outer diameter D_ppassed by the satellite shaft 18, is installed on top of the primary satellite 14U, overlapping profiles of these lower satellites, with a minimum clearance (see Fig.5, in which position 14L-1 and 14L-2 marked the bottom of the primary satellites, directly adjacent to the upper primary satellite 14U-1, overlapping profiles, and installed on site 18-1 satellite shaft).

Also in Fig.4 and 5 shows the diameter D_Lplot of the satellite shaft 18-2 running lower primary satellite 14L. Due to the different size diameters D_Uand D_Lsample plots of the satellite shafts 18-1, 18-2, the node of the planetary gear 10 with multi-level stepped arrangement of satellites, made according to the present invention, contains a set of N/2 first Signa primary satellites. The plots of the first and second satellite shafts 18-1, 18-2, have secondary satellites 16 have the same configuration. Each upper primary satellite 14U, satellite shaft 18-1 and secondary satellite 16 is preferably made, for example, by milling, as one item, as each lower primary satellite 14L together with the satellite shaft 18-2 and secondary satellite 16.

In Fig.3 shows that the upper and lower primary satellites 14U, 14L, lying in two planes of rotation, engage with the Central toothed wheel 12 in two separate areas of engagement. In Fig.5 mesh upper primary satellites 14U and the Central gear 12 shows the position 34, and the area of engagement of the lower primary satellites 14L Central gear 12 shows the position 36. In contrast to this configuration of the satellites in the conventional multi-level node of the planetary gear all of the primary satellites in contact with the Central toothed wheel in the common area of engagement.

For this version of the node of the planetary gear 10 with multi-level stepped arrangement of satellites, made according to the present invention can be achieved is wearing D_p/D_s. For this version of the node of the planetary gear 10 with multi-level stepped arrangement of satellites, in which the number of primary satellites is equal to 14, the value of the ratio of D_p/D_swell 53/79 = 0,67. For comparison, in conventional multi-level node of the planetary gear transmission described above, the value of the ratio of D_p/D_sequal to 0.31 in. Having the value of the ratio D_p/D_sequal to the node of the planetary gear 10 with multi-level stepped arrangement of the satellites of 0.67, using equations (4) to obtain the value of the index R2/P2, equal to 8.1. This suggests that the design of the gear pairs of the secondary satellites and a stationary annular gears achievable. This design is embodied in the structure are considered and shown in the drawings, the node of the planetary gear 10 with multi-level stepped arrangement of the satellites.

The analysis of Fig.4 and 6 indicates that a valid external diameter of the upper bearing 24 is limited by the distance between adjacent upper bearing 24. Even when such limit bearing life can be about 2100 hours (in the layout with twelve primary sanitarnoi gear 10 with multi-level stepped arrangement of satellites, described and reflected on the drawings, the node includes twelve primary satellites 14, six of which are upper satellites 14U and the six lower satellites 14L, located on two levels in a stepwise manner. The specialist should be clear that depending on the specific constraints on the node of the planetary gear 10 with multi-level stepped arrangement of satellites, made according to the present invention, the set of N primary satellites 14 may consist of an even number N of primary satellites 14, other than the twelve.

The present invention allows for various technical changes in terms of set design. Therefore it should be considered that the present invention within the totality of its essential features, as indicated in the attached claims, is technically feasible in a form different from the above.

1. The node of the planetary gear (10) with multilevel stepped arrangement of the satellites that contain the leading Central gear wheel (12), the set comprising N primary satellites (14) which engages with the specified Central toothed wheel (12), consisting of the first sThe second aggregate N/2 lower primary satellites (14L), moreover, the diameter of the ring gear of each of which is also equal to D_pmoreover , the upper and lower primary satellites (14U, 14L) of these populations are located on two levels in a stepwise manner, the set of N secondary satellites (16), the set of N satellite shafts (18), each of which is set corresponding to each other of the primary and secondary satellites (14, 16), the stationary annular gear wheel (20) which engages with the specified set of secondary satellites (16), and the node satellitedata (22) output power with a specified node of the planetary gear (10), mounted for rotation together with the set of N satellite shafts (18), characterized in that it is equipped with a set of upper bearings (24) and set the lower bearing (26), both of which set the specified node satellitedata (22) with the possibility of its rotation together with the specified satellite shafts (18), while the set of N satellite shafts (18) consists of a set of N/2 satellite shafts (18-2) that are related to each other above the bottom of the primary satellites (14L) and these secondary satellites (16)with each specified sa the primary satellite (14L), and population N/2 satellite shafts (18-1) that are related to each other above the top of the primary satellites (14U) and these secondary satellites, each specified satellite shaft (18-1) has a plot, the diameter of which is equal to D_uand which has the specified upper primary satellite (14U), with the specified diameter (D_uselected with minimal clearance between the specified satellite shaft (18-1) that has the specified upper primary satellite (14U) overlapping profiles directly coterminous with the specified lower primary satellites (14L), and the toothed crowns of the lower primary satellites having the specified diameter D_p.

2. The node of the planetary gear (10) under item 1, characterized in that N is equal to twelve.

3. The node of the planetary gear (10) under item 1, characterized in that it is associated with the input modules (110A, 110V) receiving power from the power plant (102A, B), which includes the first gear stage (A, B), and with the main gear (126), which includes the second gear stage (128) of the reception power of the power unit (102A, B) from the first gear stage (A, B) is mechanically connected with ) from the second gear stage (128), mechanically associated with the specified second gear stage (128) and the Central gear wheel (12) mounted for rotation specified drive shaft (130), and these input modules (110A, 110V) specified in the main gearbox (126) and the specified node of the planetary gear (10) with multilevel stepped lineup of satellites collectively form an improved transmission system (100) of the helicopter, in which the power taken from the specified node satellitedata (22) which is mechanically transmitted to the rotor shaft (106) of the helicopter.