RU2014123606A - SIDE AIRPLANE CONTROL KNOB - Google Patents
SIDE AIRPLANE CONTROL KNOB Download PDFInfo
- Publication number
- RU2014123606A RU2014123606A RU2014123606/11A RU2014123606A RU2014123606A RU 2014123606 A RU2014123606 A RU 2014123606A RU 2014123606/11 A RU2014123606/11 A RU 2014123606/11A RU 2014123606 A RU2014123606 A RU 2014123606A RU 2014123606 A RU2014123606 A RU 2014123606A
- Authority
- RU
- Russia
- Prior art keywords
- stage
- electric
- electric drive
- base
- attached
- Prior art date
Links
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Mechanical Control Devices (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
Боковая ручка управления самолетом, имеющая две вращательные степени свободы, включающая рукоятку, датчики усилия, карданный подвеса с двумя степенями подвижности, основание, два электропривода, содержащих датчик положения, электродвигатель и механические передачи, отличающаяся тем, что электроприводы выполнены в форме цилиндров, размещены один над другим так, что их продольные оси расположены под углом 90°, и образуют совместно с основанием кардан, при этом электроприводы выполнены одинаковыми, каждый электропривод содержит в себе цифровой датчик обратной связи, бескорпусной электродвигатель, механическую передачу в виде двухступенчатой волновой передачи с телами качения с выходным жестким колесом; все элементы электропривода расположены соосно, вдоль продольной оси, при этом первая ступень волновой передачи с телами качения выполнена по схеме с выходным сепаратором, вторая ступень по схеме с выходным жестким колесом, вал ротора электродвигателя связан с входным валом первой ступени волновой передачи и выполнен пустотелым, сепаратор первой ступени выполнен с центральной осью, являющийся входным звеном второй ступени, сепаратор второй ступени образует единую деталь с жестким колесом первой ступени, выполнен с пазом, в котором размещается рычаг, связывающий жесткое колесо второй ступени с валом датчика обратной связи, первый электропривод крепится к кронштейнам основания, второй электропривод через соединительную стойку крепится к жесткому колесу первого электропривода, а к жесткому колесу второго электропривода по оси, проходящий через точку пересечения осей электроприводов, крепится основаниThe side control stick of the aircraft, which has two rotational degrees of freedom, including a handle, force sensors, a gimbal with two degrees of mobility, a base, two electric drives containing a position sensor, an electric motor and mechanical transmissions, characterized in that the electric drives are made in the form of cylinders, one above the other so that their longitudinal axes are located at an angle of 90 °, and together with the base form a cardan, while the electric drives are made the same, each electric drive contains a digital feedback sensor, an open-frame electric motor, a mechanical transmission in the form of a two-stage wave transmission with rolling elements with an output hard wheel; all elements of the electric drive are located coaxially, along the longitudinal axis, while the first stage of the wave transmission with rolling elements is made according to the scheme with an output separator, the second stage according to the scheme with an output rigid wheel, the rotor shaft of the electric motor is connected to the input shaft of the first stage of the wave transmission and is made hollow, the separator of the first stage is made with a central axis, which is the input link of the second stage, the separator of the second stage forms a single part with the rigid wheel of the first stage, is made with a groove in which a lever is located connecting the rigid wheel of the second stage with the shaft of the feedback sensor, the first electric drive is attached to the base brackets, the second electric drive is attached to the rigid wheel of the first electric drive through the connecting post, and the base is attached to the rigid wheel of the second electric drive along the axis passing through the point of intersection of the axes of the electric drives
Claims (1)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
RU2014123606/11A RU2571992C1 (en) | 2014-06-10 | 2014-06-10 | Aircraft side-stick control |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
RU2014123606/11A RU2571992C1 (en) | 2014-06-10 | 2014-06-10 | Aircraft side-stick control |
Publications (2)
Publication Number | Publication Date |
---|---|
RU2014123606A true RU2014123606A (en) | 2015-12-20 |
RU2571992C1 RU2571992C1 (en) | 2015-12-27 |
Family
ID=54871112
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
RU2014123606/11A RU2571992C1 (en) | 2014-06-10 | 2014-06-10 | Aircraft side-stick control |
Country Status (1)
Country | Link |
---|---|
RU (1) | RU2571992C1 (en) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU2681462C1 (en) * | 2017-10-31 | 2019-03-06 | Акционерное общество Московский научно-производственный комплекс "Авионика" имени О.В. Успенского (АО МНПК "Авионика") | Side control stick (options) |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US278746A (en) * | 1883-06-05 | eipley | ||
US5456428A (en) * | 1993-07-21 | 1995-10-10 | Honeywell Inc. | Mechanically linked active sidesticks |
DE102010035825A1 (en) * | 2010-08-30 | 2012-03-01 | Liebherr-Aerospace Lindenberg Gmbh | Control system and apparatus for generating a virtual real-time model |
RU114939U1 (en) * | 2011-11-28 | 2012-04-20 | Федеральное государственное унитарное предприятие "Летно-исследовательский институт имени М.М. Громова" | REMOTE CONTROL DEVICE FOR Aircraft with Tactile-Pulse Signaling for the Coordination of the Control Interactions of the Crew |
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2014
- 2014-06-10 RU RU2014123606/11A patent/RU2571992C1/en active
Also Published As
Publication number | Publication date |
---|---|
RU2571992C1 (en) | 2015-12-27 |
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