RU2630269C2 - Attachment, drive and coaxial helicopter blade control assembly - Google Patents

Attachment, drive and coaxial helicopter blade control assembly Download PDF

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Publication number
RU2630269C2
RU2630269C2 RU2015150504A RU2015150504A RU2630269C2 RU 2630269 C2 RU2630269 C2 RU 2630269C2 RU 2015150504 A RU2015150504 A RU 2015150504A RU 2015150504 A RU2015150504 A RU 2015150504A RU 2630269 C2 RU2630269 C2 RU 2630269C2
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RU
Russia
Prior art keywords
rotor
swashplate
main gearbox
power
drive
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Application number
RU2015150504A
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Russian (ru)
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RU2015150504A (en
Inventor
Виктор Степанович Ермоленко
Илья Викторович Ермоленко
Андрей Вадимович Николаев
Михаил Аркадьевич Невельский
Original Assignee
Виктор Степанович Ермоленко
Михаил Аркадьевич Невельский
Андрей Вадимович Николаев
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Application filed by Виктор Степанович Ермоленко, Михаил Аркадьевич Невельский, Андрей Вадимович Николаев filed Critical Виктор Степанович Ермоленко
Priority to RU2015150504A priority Critical patent/RU2630269C2/en
Publication of RU2015150504A publication Critical patent/RU2015150504A/en
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    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C27/00Rotorcraft; Rotors peculiar thereto
    • B64C27/04Helicopters
    • B64C27/12Rotor drives
    • B64C27/14Direct drive between power plant and rotor hub
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64DEQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLYING SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D35/00Transmitting power from power plant to propellers or rotors; Arrangements of transmissions
    • B64D35/04Transmitting power from power plant to propellers or rotors; Arrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors
    • B64D35/06Transmitting power from power plant to propellers or rotors; Arrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors the propellers or rotors being counter-rotating

Abstract

FIELD: aviation.
SUBSTANCE: attachment, drive and coaxial helicopter blade control assembly comprises a main gearbox, lifting rotors, swashplates and swashplate control devices. The main gearbox housing is divided into three parts: the power part of the housing - a power plate which is fixed on the fuselage of the helicopter and to which the gearbox covers are attached from above and from below. A pipe support coaxial to the rotation axis of the lifting rotors is mounted to the power part of the main gearbox. At the upper end of the support, the upper lifting rotor is placed on the bearings, and the lower lifting rotor is located directly on the screw wheel shaft of the lower lifting rotor drive protruding beyond the gearbox. The support passes with a clearance inside the hollow shaft of the lower propeller, and the shaft of the upper lifting rotor drive passes inside the hollow support. The swashplate of the upper lifting rotor is located under the upper lifting rotor, and the swashplate of the lower lifting rotor is located above the lower lifting rotor.
EFFECT: increased reliability of the structure.
8 cl, 4 dwg

Description

The invention relates to the device of helicopters, especially coaxial, and especially unmanned.
Similar constructions are known, see, for example, US Pat. No. RU 2383470. The disadvantage of this design is the difficulty of transferring control through a fixed rod passing through the internal shaft of the rotor drive. In helicopter engineering, more than once attempts were made to combine the main rotor of the main rotors and the blade control system into one unit, but all the designs turned out to be complex and heavy.
The objective and technical result of the invention is to simplify and facilitate the design, increase its reliability.
This invention contains a main gearbox, rotors, swashplate and swashplate control device and is characterized in that:
1. The main gear case is divided into three parts: the power part of the body is the power plate, which is mounted on the fuselage of the helicopter and to which the gear covers are docked at the top and bottom, and in the cavities formed on the power plate on the rolling bearings there are gear wheels that receive rotation from the engine and rotating the lower rotor through the upper gear and the upper rotor through the lower gear, which is connected by a shaft to the hub of the upper rotor.
2. A tubular stand is mounted to the power part of the main gearbox (in this case, to the power plate), which is coaxial to the axis of rotation of the rotors, and the upper rotor is placed on bearings at the upper end of the rack, and the lower rotor is located directly on the shaft protruding beyond gear of the lower rotor drive, while the strut passes with a clearance inside the hollow shaft of the lower rotor, and the shaft of the upper rotor drive passes inside the hollow strut.
3. The stand is attached to the power part of the main gearbox using a flange or otherwise.
4. In this case, the upper rotor is driven into rotation by a shaft connecting the lower gear of the main gearbox to the hub of the upper rotor located on the bearings on the rack.
5. In this design, the upper rotor swashplate is located under the upper rotor, and the lower rotor swashplate is located above the lower rotor.
6. Moreover, between the swashplate on the rack there is a cross-body with places for mounting boosters (or actuators), for example, 6 pieces, 3 of which control the top swashplate and 3 control the bottom swashplate, and boosters (actuators) can be evenly spaced around the circumference.
In FIG. 1, 2, 3, 4 are shown: in FIG. 1 - assembly, in FIG. 2, 3 — corresponding sections along Aa and Bb, in FIG. 4, a part of this assembly is shown enlarged, including wiring of an electric power cable and control of actuators 16, 17. For the convenience of reading text and drawings, a specification is given on a separate sheet of the parts shown in the drawings and in the text.
In this design, the basis for mounting the gears 5, 6, 7, 8, for mounting the shafts of the rotors and for mounting the hollow concentric tubular stand 19 is the power plate 2. The shaft of the lower rotor is the protruding shank of the upper gear 5, and the upper the rotor is rotated by a shaft (spring) 18. The plate is attached to the fuselage of the helicopter 1 and has a top cover 4 and a bottom cover 3.
At the upper end of the strut 19 on the rolling bearings 15 there is a sleeve 20 of the upper rotor and the screw itself. The bearings 15 are closed by a cover 36. The lower gear screw sleeve 21 is fixed to the shank of the driven gear 5 by bearings 12. In FIG. 1, the lower and upper rotors are shown in the form of blades 26, sleeves 37 and torsions 24.
Under the plate 2 there is a drive spring 9, which drives the driving gears 7 and 8, the intermediate gear 32 (see Fig. 3) and, respectively, the driven gears 5 and 6. The force from the driving gears is absorbed by the bearings 10. The force from the driven gear 6 is perceived by the bearings 11. The bearings of the idler 32 are not shown.
The rotors are controlled by the swashplate: the bottom screw with the swashplate 27, and the top screw with the swashplate 28. Each swash plate consists of a ball bearing 35 fixed to the rack 19, a non-rotating housing 33, a rolling bearing 25, a rotating part of the swash plate 34 and rods for controlling the position of the blades 29. Synchronization of rotation of the rotating part of the swash plate 34 with the rotor hub is provided by a hinge-lock 30.
Between the swashplate 27 and 28 on a fixed rack 19 is a cross-case 22, which has six mounting points for the swashplate control devices (electromechanical actuators 16 and 17 are shown as an example of the latter).
To supply electric power to the actuators 16, 17 and to control them, a cable 13 is connected to each of them, for which a casing 14 is inserted into the stationary rack 19, and an annular cavity is formed between the inner surface of the rack 19 and the outer surface of the casing 14. In this case, the cables pass through the holes in the design of the main gearbox (in plate 2), enter the aforementioned annular cavity, and are connected to the actuators through the holes in the rack 19.
The unit works as follows: rotation from the drive spring 9 through the driving gears 7, 8 and through the intermediate gear 32 is transmitted to the driven gears of the lower and upper rotors 5 and 6. From the gear wheel 6, the rotation is transmitted through the shaft (spring) 18 to the hub 20 mounted on bearings 15.
Three actuators 16 evenly spaced around the circumference of the housing-crosspiece 22 control the swash plate 28 of the upper rotor (parts block 20, 24 26, 37), and three actuators 17 control the swash plate 27 of the lower rotor (parts block 21, 24 26, 37) . Helicopter is fully controlled.
Patent Specification:
Figure 00000001

Claims (8)

1. Mounting unit, drive and control the blades of a coaxial helicopter, comprising a main gearbox, rotors, swashplate and a swashplate control device, characterized in that the main gearbox housing is divided into three parts: the power part of the body is a power plate that is mounted on the fuselage the helicopter and to which the gearbox covers are attached at the top and bottom, and in the cavities formed on the power plate on the rolling bearings there are gears that receive rotation from the engine and rotate the lower s rotor through the upper gear, and resulting in rotation of the upper rotor through the lower toothed wheel, which is coupled to the hub upper shaft of the rotor.
2. The attachment, drive and control of the blades of the coaxial helicopter containing the main gearbox, rotors, swashplate and swashplate control device, characterized in that the tube is mounted to the power part of the main gearbox, located coaxially to the axis of rotation of the main rotors, and on the upper the upper rotor is placed on bearings at the end of the strut, and the lower rotor is located directly on the lower rotor drive gear shaft that extends beyond the gear reducer. and extends with clearance inside the lower hollow shaft of the propeller, and extends inside the hollow rack drive shaft of the upper rotor.
3. The node according to claim 2, characterized in that the tubular rack is attached to the power part of the main gearbox using a flange.
4. The assembly according to claim 2, characterized in that the upper rotor is rotated by a shaft connecting the lower gear of the main gearbox with the upper rotor bush located on the bearing pillar.
5. The node according to claim 2, characterized in that the swashplate of the upper rotor is located under the top rotor, and the swashplate of the lower rotor is located above the lower rotor.
6. The node according to claim 5, characterized in that between the swashplate on the rack there is a cross-body with places for mounting boosters or actuators, for example, 6 pieces, 3 of which control the upper swashplate and 3 control the lower swashplate.
7. The node according to claim 6, characterized in that the boosters or actuators are evenly spaced around the circumference.
8. The node according to claim 6, characterized in that for supplying electrical power to the boosters or actuators and for controlling them, a cable is connected to each of them, for which a casing is inserted into the stationary rack, while between the inner surface of the rack and the outer surface of the casing an annular cavity is formed, and the design of the main gearbox has drilling.
RU2015150504A 2015-11-25 2015-11-25 Attachment, drive and coaxial helicopter blade control assembly RU2630269C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2015150504A RU2630269C2 (en) 2015-11-25 2015-11-25 Attachment, drive and coaxial helicopter blade control assembly

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2015150504A RU2630269C2 (en) 2015-11-25 2015-11-25 Attachment, drive and coaxial helicopter blade control assembly

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RU2015150504A RU2015150504A (en) 2017-05-29
RU2630269C2 true RU2630269C2 (en) 2017-09-06

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2729900C1 (en) * 2019-12-30 2020-08-13 Акционерное общество "Камов" Drive system of coaxial rotors of helicopter with support mast

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2265554C1 (en) * 2004-04-01 2005-12-10 Открытое акционерное общество "Камов" Helicopter with coaxial main rotors
RU2383470C2 (en) * 2007-04-16 2010-03-10 Общество с ограниченной ответственностью "Ротор-В" Two-rotor coaxial system with mirrored swash plates
CN102658865A (en) * 2012-05-17 2012-09-12 李游 Coaxial drive and control structure for coaxial contrarotation rotor helicopter
US20140312177A1 (en) * 2013-04-18 2014-10-23 Rajesh Gaonjur Coaxial rotor/wing aircraft
RU2541569C1 (en) * 2013-08-08 2015-02-20 Андрей Михайлович Трубицин Coaxial-rotor helicopter gearbox

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2265554C1 (en) * 2004-04-01 2005-12-10 Открытое акционерное общество "Камов" Helicopter with coaxial main rotors
RU2383470C2 (en) * 2007-04-16 2010-03-10 Общество с ограниченной ответственностью "Ротор-В" Two-rotor coaxial system with mirrored swash plates
CN102658865A (en) * 2012-05-17 2012-09-12 李游 Coaxial drive and control structure for coaxial contrarotation rotor helicopter
US20140312177A1 (en) * 2013-04-18 2014-10-23 Rajesh Gaonjur Coaxial rotor/wing aircraft
RU2541569C1 (en) * 2013-08-08 2015-02-20 Андрей Михайлович Трубицин Coaxial-rotor helicopter gearbox

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2729900C1 (en) * 2019-12-30 2020-08-13 Акционерное общество "Камов" Drive system of coaxial rotors of helicopter with support mast
RU2729900C9 (en) * 2019-12-30 2020-11-26 Акционерное общество "Национальный центр вертолетостроения им. М.Л. Миля и Н.И. Камова" (АО "НЦВ Миль и Камов") Drive system of coaxial rotors of helicopter with support mast

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Effective date: 20171129