WO2014142773A1 - Drive for controlling a moveable aerodynamic surface of an aircraft wing - Google Patents
Drive for controlling a moveable aerodynamic surface of an aircraft wing Download PDFInfo
- Publication number
- WO2014142773A1 WO2014142773A1 PCT/UA2013/000058 UA2013000058W WO2014142773A1 WO 2014142773 A1 WO2014142773 A1 WO 2014142773A1 UA 2013000058 W UA2013000058 W UA 2013000058W WO 2014142773 A1 WO2014142773 A1 WO 2014142773A1
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- WIPO (PCT)
- Prior art keywords
- aircraft
- aerodynamic surface
- drive
- wing
- rotation
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/24—Transmitting means
- B64C13/26—Transmitting means without power amplification or where power amplification is irrelevant
- B64C13/28—Transmitting means without power amplification or where power amplification is irrelevant mechanical
Definitions
- the present invention relates to aircraft flight control systems, and more particularly, to a drive for controlling the moving aerodynamic surfaces of an aircraft wing, such as flaps and / or ailerons.
- the drive control the movable aerodynamic surface of the wing of the aircraft which is attached to the stationary relative to the fuselage of the aerodynamic surface of the wing of the aircraft with the possibility of its rotation (rotation) and includes a mover mounted in the cavity stationary relative to the fuselage of the aerodynamic surface of the wing of the aircraft link connected to the moving aerodynamic surface of the wing of the aircraft [RF Patent N ° 244272 1, MP ⁇ 64 ⁇ 13/42 (2006.01), Published: 02/20/2012].
- a feature of this drive is the use of a two-stage wave transmission in it, the rotating link of which is made in the form of a hollow shaft with a flange mounted on a movable aerodynamic surface.
- a drive containing a powerful electric motor with a rotor speed of 5000-25000 min- 1 the shaft of which is connected through a two-stage wave gear with a movable aerodynamic surface, is a rather complex, heavy and not sufficiently reliable design.
- This conclusion is based on the fact that the principle of wave transmission is based on the cyclical excitation of deformation waves in the elastic transmission element, and therefore the operational capabilities of the wave transmission depend on the temperature stability air surrounding the gearbox.
- the aircraft and its structural elements are exposed to temperature fluctuations in the range from +60 (at the aerodrome) to -70 ° C (in flight), and therefore the wave-transmission metal accumulates thermal fatigue during operation, which can lead to the destruction of elastic transmission element, which reduces the reliability of the specified drive as a whole and adversely affects the safety of the aircraft.
- the basis of the invention is the task of creating such a drive control the movable aerodynamic surface of the wing of the aircraft, which would be simpler and more reliable.
- the problem is solved by creating conditions for the rotation of the moving aerodynamic surface of the aircraft by its interaction with the bend of the torsion which rotates (rotates) around its axis,
- the proposed, as well as the known drive control of the moving aerodynamic surface of the wing of the aircraft, which is attached to the stationary relative to the fuselage of the aerodynamic surface of the wing of the aircraft with the possibility of its rotation (rotation), includes installed in the cavity stationary relative to the fuselage of the aerodynamic surface of the wing of the aircraft mover with an output rotating link connected the movable aerodynamic surface of the wing of the aircraft, and, according to the invention, a servo drive is used as a propeller, the output rotating link of which is made in the form of at least one torsion bar, one end of which is connected to the servo drive shaft and passes through a thrust bearing and a roller mounted in a sliding bearing, which has a rectangular slot, the torsion bar contains at least one bend, the rotation axis which coincides with the axis of rotation of the moving aerodynamic surface of the wing of the aircraft and is installed in the roller of the sliding bearing with the possibility of describing the conical surface and, by interacting with the moving aero yna
- a torsion bar is a spring in the form of a shaft that works for torsion, that is, a shaft that has a predicted value of torsion resistance.
- parameters are set for changing the angular position of the moving aerodynamic surface of the wing of the aircraft — flaps and / or ailerons.
- the torsion bar due to the predicted value of torsion resistance, absorbs peak loads and provides a change in the angular position of the moving aerodynamic surface of the wing of the aircraft without damaging it.
- the technical result obtained as a result of the implementation of the present invention is to create conditions for rotation of the moving aerodynamic surface of the aircraft by the interaction of its predetermined section with the bend of the torsion bar.
- one end of the torsion bar is connected to the servo shaft, the other is installed in the bearing, and the torsion bar can rotate around its axis by the angle specified by the pilot under the action of the servo drive.
- the proposed drive control the movable aerodynamic surface of the wing of the aircraft consists of structural elements, for the manufacture of which are used today known techniques, devices and materials.
- the drive control of the moving aerodynamic surface of the wing of an aircraft can be used in aircraft designed to transport passengers and goods for various industries and agriculture, and therefore we can conclude that the proposed solution meets the criteria of the invention "industrial applicability".
- Figure 1 shows a side view of the proposed drive.
- Figure 2 shows a top view of the proposed drive.
- FIG.Z 4 shows the robot of the proposed drive located in the cavity of the wing.
- FIG. Figures 5, 6, 7, 8 show the dependences of the torque (M) that occurs in the drive mechanism of two different executive systems - with and without torsion under the same loading conditions.
- the proposed drive consists of a servo drive 2, a torsion 3 and a thrust bearing 4 mounted in a cavity fixed relative to the fuselage of the aerodynamic surface of the wing of an airplane 1 (hereinafter referred to as the wing 1).
- the movable aerodynamic surfaces of the wing 5 and 6 are pivotally connected to the wing 1 and provided with bearings installed in their cavities sliding 7 and 8, respectively, In each bearing 7 and 8 there is a rectangular slot in which the roller 9 is placed with the possibility of rotation on the torsion bar 3, which passes through them.
- Torsion 3 may contain one or two bends - depending on the number of movable aerodynamic surfaces 5 and 6 and passes from the servo drive 2 through the thrust bearing 4 to the sliding bearings 7 and 8.
- the bending sections of the torsion 3 coincide with the rotation (rotation) axes 10 and 1 1 movable aerodynamic surfaces 5 and 6.
- the drive is provided with a servo control unit - a programmed logic controller (PLC) and a servo angle sensor / not shown /.
- PLC programmed logic controller
- the geometric parameters of torsion 3 and its bends, the material for manufacturing the torsion, and the correspondence of the angle of rotation of the shaft of the servo drive 2 to the angle of each bend relative to the axis of the torsion 3 are determined by experimental-calculation method, providing a condition under which the place of bending of the torsion bar must coincide with the axis of rotation of the movable aerodynamic surface 5 or 6.
- gear drive Part of the manufactured drive together with the servo drive 2 is installed in the cavity of the wing 1, and the other in the cavities of the movable aerodynamic surfaces 5 and 6.
- the control unit for the servo drive can be placed in the fuselage or in the cockpit.
- a signal is received that initiates the rotation of the shaft of the servo drive 2.
- the shaft of the servo drive 2 rotating around its axis, forces each bend of the torsion 3, which rotates, to describe the conical surface in space, but, due to interaction with the corresponding movable aerodynamic surfaces 5 and 6 of the wing of the aircraft, change their angular position.
- Fig.5 and Fig.6 depicts, respectively, a direct drive of the aerodynamic surface 5 from the servo drive 2 and using torsion 3 of the proposed drive.
- the torque the moment Ml increases linearly with increasing inclination of the aerodynamic surface 5, due to the fact that the shoulder of the force 1/2 L remains unchanged while the force F increases.
- the force F increases, and the shoulder of the force B decreases from the maximum value to zero, which together leads to an inverted parabolic dependence of the moment M2.
- Fig. 5 and Fig. B for simplicity, a case with one movable aerodynamic surface is considered.
- Wing 1 and movable aerodynamic surfaces 5 and 6 do not require reinforced hinges and other structural elements for their interaction, and therefore can be made even of plastic with a porous filler.
- a servo drive can be used, both with a full angle of rotation (rotation), and with a limited one.
- the size of the bearings 7 and 8 can be reduced.
- Torsion 3 can be made of ordinary spring-spring steel, which ensures its reliable operation in the temperature range from +60 to -70 ° C.
Abstract
The invention relates to aviation, to systems for controlling the flight of an aircraft, and more specifically to a drive for controlling moveable aerodynamic surfaces of an aircraft wing such as flaps and/or ailerons. The drive comprises a propeller which is mounted in the cavity of an aerodynamic surface of an aircraft wing which is immoveable relative to the fuselage, said propeller having a rotating output component which is connected to the moveable aerodynamic surface of the aircraft wing, and, in accordance with the invention, a servo drive is used as propeller, wherein the rotating output component of said servo drive is in the form of at least one torsion bar, one end of which is connected to the shaft of the servo drive and passes through a support bearing and a roller which is mounted in a sliding bearing having a rectangular slot, wherein the torsion bar comprises at least one bend having an axis of rotation which coincides with the axis of rotation of the moveable aerodynamic surface of the aircraft wing, and is mounted in the roller of the sliding bearing so as to provide the possibility of said bend describing a conical surface and of interacting with the moveable aerodynamic surface of the aircraft wing and changing the angular position thereof. The aim of the invention is to produce a drive which is simpler and more reliable. This aim is achieved by virtue of producing conditions for the rotation of a moveable aerodynamic surface of an aircraft by means of the interaction of said surface with a bend in a torsion bar which rotates (revolves) around its axis.
Description
Привод управления подвижной аэродинамической Movable aerodynamic control drive
поверхностью крыла самолета. wing surface of an airplane.
Предлагаемое изобретение относится к системам управления полетом самолета, а более конкретно - к приводу управления подвижными аэродинамическими поверхностями крыла самолета такими, как закрылки и/или элероны. The present invention relates to aircraft flight control systems, and more particularly, to a drive for controlling the moving aerodynamic surfaces of an aircraft wing, such as flaps and / or ailerons.
Наиболее близким к предлагаемому по количеству существенных признаков является привод управления подвижной аэродинамической поверхностью крыла самолета, которая присоединена к неподвижной относительно фюзеляжа аэродинамической поверхности крыла самолета с возможностью ее вращения (поворота) и включает установленный в полости неподвижной относительно фюзеляжа аэродинамической поверхности крыла самолета движитель с выходным вращающимся звеном, соединенным с подвижной аэродинамической поверхностью крыла самолета [Патент РФ N° 2442721, МП В64С 13/42 (2006.01), Опубликовано: 20.02.2012]. Closest to the proposed one by the number of essential features is the drive control the movable aerodynamic surface of the wing of the aircraft, which is attached to the stationary relative to the fuselage of the aerodynamic surface of the wing of the aircraft with the possibility of its rotation (rotation) and includes a mover mounted in the cavity stationary relative to the fuselage of the aerodynamic surface of the wing of the aircraft link connected to the moving aerodynamic surface of the wing of the aircraft [RF Patent N ° 244272 1, MP В64С 13/42 (2006.01), Published: 02/20/2012].
Особенностью указанного привода является применение в нем двухступенчатой волновой передачи, вращающееся звено которой изготовлено в виде полого вала с фланцем, закрепленным на подвижной аэродинамической поверхности. Но привод, содержащий мощный электродвигатель с частотой вращения ротора 5000-25000 минуту' 1, вал которого соединен через двухступенчатый волновой редуктор с подвижной аэродинамической поверхностью, является довольно сложной, тяжелой и недостаточно надежной конструкцией. Этот вывод основан на том, что принцип работы волновой передачи базируется на циклическом возбуждении волн деформации в упругом элементе передачи, а поэтому эксплуатационные возможности волновой передачи зависят от стабильности температуры
воздуха, окружающего редуктор. В то же время самолет и его конструктивные элементы подвергаются воздействию колебаний температуры в диапазоне от +60 (на аэродроме) до -70°С (в полете), а потому металл волновой передачи в процессе эксплуатации накапливает термическую усталость, которая может приводить к разрушению упругого элемента передачи, что снижает надежность указанного привода в целом и негативно сказывается на безопасности воздушного судна. A feature of this drive is the use of a two-stage wave transmission in it, the rotating link of which is made in the form of a hollow shaft with a flange mounted on a movable aerodynamic surface. But a drive containing a powerful electric motor with a rotor speed of 5000-25000 min- 1 , the shaft of which is connected through a two-stage wave gear with a movable aerodynamic surface, is a rather complex, heavy and not sufficiently reliable design. This conclusion is based on the fact that the principle of wave transmission is based on the cyclical excitation of deformation waves in the elastic transmission element, and therefore the operational capabilities of the wave transmission depend on the temperature stability air surrounding the gearbox. At the same time, the aircraft and its structural elements are exposed to temperature fluctuations in the range from +60 (at the aerodrome) to -70 ° C (in flight), and therefore the wave-transmission metal accumulates thermal fatigue during operation, which can lead to the destruction of elastic transmission element, which reduces the reliability of the specified drive as a whole and adversely affects the safety of the aircraft.
Поэтому в основу предлагаемого изобретения поставлена задача создания такого привода управления подвижной аэродинамической поверхностью крыла самолета, который был бы более простым и надежным. Поставленная задача решается за счет создания условий для поворота подвижной аэродинамической поверхности самолета путем ее взаимодействия с изгибом торсиона, совершающего вращение (поворот) вокруг своей оси, Therefore, the basis of the invention is the task of creating such a drive control the movable aerodynamic surface of the wing of the aircraft, which would be simpler and more reliable. The problem is solved by creating conditions for the rotation of the moving aerodynamic surface of the aircraft by its interaction with the bend of the torsion which rotates (rotates) around its axis,
Предлагаемый, как и известный привод управления подвижной аэродинамической поверхностью крыла самолета, которая присоединена к неподвижной относительно фюзеляжа аэродинамической поверхности крыла самолета с возможностью ее вращения (поворота), включает установленный в полости неподвижной относительно фюзеляжа аэродинамической поверхности крыла самолета движитель с выходным вращающимся звеном, соединенным с подвижной аэродинамической поверхностью крыла самолета, а, согласно изобретению, в качестве движителя применен сервопривод, выходное вращающееся звено которого выполнено в виде, по меньшей мере, одного торсиона, один конец которого соединен с валом сервопривода и проходит через опорный подшипник и ролик, установленный в подшипнике скольжения, который имеет прямоугольную прорезь, торсион содержит, как минимум один изгиб, ось вращения которого совпадает с осью вращения подвижной аэродинамической поверхности крыла самолета и установлен в ролике подшипника скольжения с возможностью описывания им конической поверхности и, путем взаимодействия с подвижной аэродинамической поверхностью крыла самолета, изменения ее углового положения.
Сервопривод (следящий привод) — привод с управлением через отрицательную обратную связь, которая позволяет точно управлять параметрами движения, благодаря обеспечению его датчиком угла поворота выходного вала редуктора (энкодером). The proposed, as well as the known drive control of the moving aerodynamic surface of the wing of the aircraft, which is attached to the stationary relative to the fuselage of the aerodynamic surface of the wing of the aircraft with the possibility of its rotation (rotation), includes installed in the cavity stationary relative to the fuselage of the aerodynamic surface of the wing of the aircraft mover with an output rotating link connected the movable aerodynamic surface of the wing of the aircraft, and, according to the invention, a servo drive is used as a propeller, the output rotating link of which is made in the form of at least one torsion bar, one end of which is connected to the servo drive shaft and passes through a thrust bearing and a roller mounted in a sliding bearing, which has a rectangular slot, the torsion bar contains at least one bend, the rotation axis which coincides with the axis of rotation of the moving aerodynamic surface of the wing of the aircraft and is installed in the roller of the sliding bearing with the possibility of describing the conical surface and, by interacting with the moving aero ynamic aircraft wing surface, changes its angular position. Servo drive (servo drive) - a drive with control via negative feedback, which allows you to precisely control the parameters of the movement, thanks to providing it with a sensor for the rotation angle of the output shaft of the gearbox (encoder).
Торсион - это пружина в виде вала, который работает на кручение, то есть вал, который имеет прогнозированное значение сопротивления кручению. A torsion bar is a spring in the form of a shaft that works for torsion, that is, a shaft that has a predicted value of torsion resistance.
При этом путем задания определенных параметров торсиону и его изгибу, а также соответствующего поворота валу сервопривода и вместе с ним торсиону, задают параметры изменения углового положения подвижной аэродинамической поверхности крыла самолета - закрылкам и/или элеронам. In this case, by setting certain parameters to the torsion bar and its bend, as well as corresponding rotation to the servo shaft and with it the torsion bar, parameters are set for changing the angular position of the moving aerodynamic surface of the wing of the aircraft — flaps and / or ailerons.
Торсион, за счет прогнозированного значения сопротивлению кручению, поглощает пиковые нагрузки и обеспечивает изменение углового положения подвижной аэродинамической поверхности крыла самолета не повреждая ее. The torsion bar, due to the predicted value of torsion resistance, absorbs peak loads and provides a change in the angular position of the moving aerodynamic surface of the wing of the aircraft without damaging it.
Во время проведения патентно-информационных исследований при подготовке настоящей заявки авторами не обнаружены конструкции приводов управления подвижной аэродинамической поверхностью крыла самолета с указанной выше совокупностью существенных признаков, что доказывает соответствие заявляемых технических решений критерию изобретения "новизна", During the conduct of patent information research in the preparation of this application, the authors did not find the design of actuators for controlling the mobile aerodynamic surface of the wing of the aircraft with the above set of essential features, which proves the conformity of the claimed technical solutions to the criteria of the invention of "novelty",
Технический результат, полученный в результате осуществления предлагаемого изобретения, состоит в создании условий для поворота подвижной аэродинамической поверхности самолета путем взаимодействия ее заданного участка с изгибом торсиона. Один конец торсиона, при этом, соединен с валом сервопривода, другой - установлен в подшипнике, а торсион под действием сервопривода может совершать поворот вокруг своей оси на заданный пилотом угол. The technical result obtained as a result of the implementation of the present invention is to create conditions for rotation of the moving aerodynamic surface of the aircraft by the interaction of its predetermined section with the bend of the torsion bar. At the same time, one end of the torsion bar is connected to the servo shaft, the other is installed in the bearing, and the torsion bar can rotate around its axis by the angle specified by the pilot under the action of the servo drive.
Указанный технический результат в известных технических решениях, которые вошли в уровень техники, авторами не выявлен, поэтому
предлагаемый привод управления подвижной аэродинамической поверхностью крыла самолета может быть признан соответствующим критерию изобретения "изобретательский уровень". The specified technical result in the known technical solutions that are included in the prior art, the authors have not identified, therefore the proposed drive control the movable aerodynamic surface of the wing of the aircraft can be recognized as meeting the criteria of the invention "inventive step".
Предлагаемый привод управления подвижной аэродинамической поверхностью крыла самолета состоит из конструктивных элементов, для изготовления которых используют известные на сегодняшний день технологические приемы, устройства и материалы. Привод управления подвижной аэродинамической поверхностью крыла самолета может быть использован в летательных аппаратах, предназначенных для транспортирования пассажиров и грузов для различных отраслей промышленности и сельского хозяйства, а поэтому можно сделать вывод о том, что предлагаемое решение соответствует критерию изобретения «промышленная применимость». The proposed drive control the movable aerodynamic surface of the wing of the aircraft consists of structural elements, for the manufacture of which are used today known techniques, devices and materials. The drive control of the moving aerodynamic surface of the wing of an aircraft can be used in aircraft designed to transport passengers and goods for various industries and agriculture, and therefore we can conclude that the proposed solution meets the criteria of the invention "industrial applicability".
Суть предлагаемого изобретения объясняется схематическими чертежами. The essence of the invention is explained by schematic drawings.
На фиг.1 показан вид сбоку на предлагаемый привод. Figure 1 shows a side view of the proposed drive.
На фиг.2 показан вид сверху на предлагаемый привод. Figure 2 shows a top view of the proposed drive.
На фиг.З, 4 показана робота предлагаемого привода, расположенного в полости крыла. In Fig.Z, 4 shows the robot of the proposed drive located in the cavity of the wing.
На фиг. 5, 6, 7, 8 показаны зависимости крутящего момента (М), который возникает в механизме привода двух разных исполнительных систем - с использованием торсиона и без него при одинаковых условиях нагружения. In FIG. Figures 5, 6, 7, 8 show the dependences of the torque (M) that occurs in the drive mechanism of two different executive systems - with and without torsion under the same loading conditions.
Предлагаемый привод состоит из установленного в полости неподвижной относительно фюзеляжа аэродинамической поверхности крыла самолета 1 (далее крыла 1 ) сервопривода 2, торсиона 3 и опорного подшипника 4. Подвижные аэродинамические поверхности крыла 5 и 6 шарнирно соединены с крылом 1 и обеспечены, установленными в их полостях подшипниками скольжения 7 и 8, соответственно, В каждом подшипнике 7 и 8 имеется прямоугольная прорезь, в которой размещен ролик 9 с возможностью вращения на торсионе 3, который проходит через них.
Торсион 3 может содержать один или два изгиба - в зависимости от количества подвижных аэродинамических поверхностей 5 и 6 и проходит от сервопривода 2 через опорный подшипник 4 в подшипники скольжения 7 и 8. Участки изгиба торсиона 3 совпадают с осями 10 и 1 1 вращения (поворота) подвижных аэродинамических поверхностей 5 и 6. Привод обеспечен блоком управления сервоприводом - программированным логическим контролером (ПЛК) и датчиком угла поворота вала сервопривода /не показано/. The proposed drive consists of a servo drive 2, a torsion 3 and a thrust bearing 4 mounted in a cavity fixed relative to the fuselage of the aerodynamic surface of the wing of an airplane 1 (hereinafter referred to as the wing 1). The movable aerodynamic surfaces of the wing 5 and 6 are pivotally connected to the wing 1 and provided with bearings installed in their cavities sliding 7 and 8, respectively, In each bearing 7 and 8 there is a rectangular slot in which the roller 9 is placed with the possibility of rotation on the torsion bar 3, which passes through them. Torsion 3 may contain one or two bends - depending on the number of movable aerodynamic surfaces 5 and 6 and passes from the servo drive 2 through the thrust bearing 4 to the sliding bearings 7 and 8. The bending sections of the torsion 3 coincide with the rotation (rotation) axes 10 and 1 1 movable aerodynamic surfaces 5 and 6. The drive is provided with a servo control unit - a programmed logic controller (PLC) and a servo angle sensor / not shown /.
Предварительно, до установки предлагаемого привода в полости крыла самолета экспериментально-расчетным методом определяют геометрические параметры торсиона 3 и его изгибов, материал для изготовления торсиона, а таюке соответствие значения угла поворота вала сервопривода 2 углу каждого изгиба относительно оси торсиона 3, обеспечивая условие, при котором место изгиба торсиона должно совпадать с осью вращения подвижной аэродинамической поверхности 5 или 6. После определения указанных параметров в соответствии с ними изготавливают предлагаемый привод. Часть изготовленного привода вместе с сервоприводом 2 устанавливают в полости крыла 1 , а другую - в полостях подвижных аэродинамических поверхностей 5 и 6. Блок управления сервоприводом может быть размещен в фюзеляже или в кабине пилота. Previously, before installing the proposed drive in the wing cavity of the aircraft, the geometric parameters of torsion 3 and its bends, the material for manufacturing the torsion, and the correspondence of the angle of rotation of the shaft of the servo drive 2 to the angle of each bend relative to the axis of the torsion 3 are determined by experimental-calculation method, providing a condition under which the place of bending of the torsion bar must coincide with the axis of rotation of the movable aerodynamic surface 5 or 6. After determining these parameters in accordance with them, the following conditions are made: gear drive. Part of the manufactured drive together with the servo drive 2 is installed in the cavity of the wing 1, and the other in the cavities of the movable aerodynamic surfaces 5 and 6. The control unit for the servo drive can be placed in the fuselage or in the cockpit.
Предлагаемый привод работает так. The proposed drive works like this.
Из блока управления сервоприводом в сервопривод 2 поступает сигнал, который инициирует вращение вала сервопривода 2. Вал сервопривода 2, совершая вращение вокруг своей оси, заставляет каждый изгиб торсиона 3, который вращается, описывать в пространстве коническую поверхность, а, благодаря взаимодействию с соответствующими подвижными аэродинамическими поверхностями 5 и 6 крыла самолета, изменять их угловое положение. From the servo control unit to the servo drive 2, a signal is received that initiates the rotation of the shaft of the servo drive 2. The shaft of the servo drive 2, rotating around its axis, forces each bend of the torsion 3, which rotates, to describe the conical surface in space, but, due to interaction with the corresponding movable aerodynamic surfaces 5 and 6 of the wing of the aircraft, change their angular position.
На фиг.5 и фиг.6 изображены, соответственно, непосредственный привод аэродинамической поверхности 5 от сервопривода 2 и при помощи торсиона 3 предлагаемого привода. В первом варианте (фиг.5) крутящий
момент Ml линейно возрастает при увеличении угла наклона аэродинамической поверхности 5, благодаря тому, что плечо силы 1/2 L остается неизменным в то время, как сила F увеличивается. Во втором варианте (фиг.б), при увеличении угла наклона аэродинамической поверхности 5 сила F увеличивается, а плечо силы В уменьшается от максимального значения до нуля, что совместно приводит к получению перевернутой параболической зависимости момента М2. На фиг.5 и фиг.б для упрощения рассмотрен случай с одной подвижной аэродинамической поверхностью. In Fig.5 and Fig.6 depicts, respectively, a direct drive of the aerodynamic surface 5 from the servo drive 2 and using torsion 3 of the proposed drive. In the first embodiment (Fig. 5), the torque the moment Ml increases linearly with increasing inclination of the aerodynamic surface 5, due to the fact that the shoulder of the force 1/2 L remains unchanged while the force F increases. In the second embodiment (Fig. B), with an increase in the angle of inclination of the aerodynamic surface 5, the force F increases, and the shoulder of the force B decreases from the maximum value to zero, which together leads to an inverted parabolic dependence of the moment M2. In Fig. 5 and Fig. B, for simplicity, a case with one movable aerodynamic surface is considered.
Анализ сил, которые возникают в предлагаемом приводе во время поворота поверхностей 5 и 6, показывает выигрыш по силе примерно в два раза по сравнению с приводом-прототипом, что позволяет существенно уменьшить вес предлагаемого привода. Крыло 1 и подвижные аэродинамические поверхности 5 и 6 не требуют для их взаимодействия усиленных шарниров и других конструктивных элементов, а потому могут быть изготовлены, даже из пластика с пористым наполнителем. Analysis of the forces that occur in the proposed drive during the rotation of surfaces 5 and 6 shows a gain in strength of about two times compared with the prototype drive, which can significantly reduce the weight of the proposed drive. Wing 1 and movable aerodynamic surfaces 5 and 6 do not require reinforced hinges and other structural elements for their interaction, and therefore can be made even of plastic with a porous filler.
В предлагаемом приводе может быть использован сервопривод, как с полным углом поворота (вращения), так и с ограниченным. При использовании сервопривода с ограниченным углом поворота размер подшипников скольжения 7 и 8 может быть уменьшен. In the proposed drive, a servo drive can be used, both with a full angle of rotation (rotation), and with a limited one. When using a servo with a limited angle of rotation, the size of the bearings 7 and 8 can be reduced.
Торсион 3 может быть изготовлен из обычной рессорно-пружинной стали, которая обеспечивает его надежную работу в температурном диапазоне от +60 до -70°С. Torsion 3 can be made of ordinary spring-spring steel, which ensures its reliable operation in the temperature range from +60 to -70 ° C.
Поскольку предлагаемая конструкция более простая, она является и более надежной, чем конструкция-прототип.
Since the proposed design is simpler, it is more reliable than the prototype design.
Claims
Формула изобретения. Claim.
Привод управления подвижной аэродинамической поверхностью крыла самолета, которая присоединена к неподвижной относительно фюзеляжа аэродинамической поверхности крыла самолета с возможностью ее вращения (поворота), который включает установленный в полости неподвижной относительно фюзеляжа аэродинамической поверхности крыла самолета движитель с выходным вращающимся звеном, соединенным с подвижной аэродинамической поверхностью крыла самолета, отличающийся тем, что в качестве движителя применен сервопривод, выходное вращающееся звено которого выполнено в виде, по меньшей мере, одного торсиона, один конец которого соединен с валом сервопривода и проходит через опорный подшипник и ролик, установленный в подшипнике скольжения, который имеет прямоугольную прорезь, торсион содержит, как минимум один изгиб, ось вращения которого совпадает с осью вращения подвижной аэродинамической поверхности крыла самолета и установлен в ролике подшипника скольжения с возможностью описывания им конической поверхности и взаимодействия с подвижной аэродинамической поверхностью крыла самолета и изменения ее углового положения.
The control drive of the movable aerodynamic surface of the wing of the aircraft, which is attached to the aerodynamic surface of the wing of the aircraft stationary relative to the fuselage with the possibility of rotation (rotation), which includes a propeller mounted in the cavity of the aerodynamic surface of the wing of the aircraft stationary relative to the fuselage, with an output rotating link connected to the movable aerodynamic surface of the wing aircraft, characterized in that as a propulsion applied servo, output rotating sound which is made in the form of at least one torsion bar, one end of which is connected to the servo shaft and passes through a thrust bearing and a roller mounted in a sliding bearing, which has a rectangular slot, the torsion bar contains at least one bend whose rotation axis coincides with the axis of rotation of the movable aerodynamic surface of the wing of the aircraft and is mounted in the roller of the sliding bearing with the possibility of describing the conical surface and interaction with the movable aerodynamic surface of the wings and aircraft and changes in its angular position.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| UAU201303055 | 2013-03-12 | ||
| UAU201303055U UA79830U (en) | 2013-03-12 | 2013-03-12 | Control drive of moving aircraft airfoil wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| WO2014142773A1 true WO2014142773A1 (en) | 2014-09-18 |
Family
ID=51537221
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/UA2013/000058 WO2014142773A1 (en) | 2013-03-12 | 2013-06-10 | Drive for controlling a moveable aerodynamic surface of an aircraft wing |
Country Status (2)
| Country | Link |
|---|---|
| UA (1) | UA79830U (en) |
| WO (1) | WO2014142773A1 (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3958779A (en) * | 1975-05-27 | 1976-05-25 | Fairchild Industries Inc. | Aircraft control system with a jam isolating coupling |
| US6244542B1 (en) * | 1999-07-20 | 2001-06-12 | Northrop Grumman Corporation | Rotor driven edge |
| RU2296694C2 (en) * | 2001-11-28 | 2007-04-10 | Нортроп Грамман Корпорейшн | Aerodynamic surface control system |
| US20090159755A1 (en) * | 2007-12-21 | 2009-06-25 | Airbus Espana, S.L. | Aircraft control device |
-
2013
- 2013-03-12 UA UAU201303055U patent/UA79830U/en unknown
- 2013-06-10 WO PCT/UA2013/000058 patent/WO2014142773A1/en active Application Filing
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3958779A (en) * | 1975-05-27 | 1976-05-25 | Fairchild Industries Inc. | Aircraft control system with a jam isolating coupling |
| US6244542B1 (en) * | 1999-07-20 | 2001-06-12 | Northrop Grumman Corporation | Rotor driven edge |
| RU2296694C2 (en) * | 2001-11-28 | 2007-04-10 | Нортроп Грамман Корпорейшн | Aerodynamic surface control system |
| US20090159755A1 (en) * | 2007-12-21 | 2009-06-25 | Airbus Espana, S.L. | Aircraft control device |
Also Published As
| Publication number | Publication date |
|---|---|
| UA79830U (en) | 2013-04-25 |
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