(57) Abstract:The invention relates to the field of unmanned aerial vehicles and can be used in the development of actuators aerodynamic rudders. The unit consists of four actuators, mounted on the inner surface of the fuselage 19. Each mechanism has a housing 1, a shaft 2 aerodynamic steering, the electric motor 5, a sensor 6 position of the steering wheel and the gearbox of the three series-connected cylindrical gears, ball screw transmission and transfer to a rack and pinion gearing. The sensor 6 is connected with the shaft 2 using a spatial Cam mechanism. The invention is directed to increasing the load capacity, torsional rigidity and stiffness of the mounting actuators to the fuselage of the aircraft. 4 C.p. f-crystals, 2 Il. The invention relates to the field of unmanned aerial vehicles and can be used in the development of actuators aerodynamic rudders.Known block steering aerodynamic rudders unmanned aerial vehicles, consisting of four actuators located in the volume, which is limited to the inner surface of the fuselage, Each actuator has a housing, which is installed in the fuselage by means of the connection node, the shaft aerodynamic steering, which is mounted on supports rotation, the electric motor, which shaft through the reduction gear is connected with the shaft aerodynamic steering wheel position sensor specified steering, which is connected kinematic chain with said steering shaft (Krymov C. G., Rabinovich L. C., Steblov Century, actuators, control systems of aircraft. M. , engineering, 1987, page 164, Fig. 4.1.).The disadvantage of the described construction is the large building height actuators, due to the large number of stages in the gearbox (5 - 6 steps) that does not allow you to build actuators so as to reduce their volume to the size required for unit control surface actuators in the above volume.Known also block control surface actuators placed in the volume, which is limited to the inner cylindrical surface of the fuselage of the aircraft and coaxially located outer surface of gazivoda jet engine containing four actuator. Each actuator has a housing, which is installed in the fuselage posreal which through a gear connected with said steering shaft, the position sensor mentioned steering, which is connected kinematic chain with said steering shaft. Mentioned the gearbox consists of three types of series-connected transmission - conical, cylindrical and wave. Wave transmission is performed on a two symmetric scheme (Patent RF N 2102282 MKI B 64 C 13/34).The above block of steering actuators is taken as a prototype.The layout and design of the unit control surface actuators described in the prototype, provide building height actuators to sizes comparable with the diameter of the motor, which allows you to set the unit control surface actuators in the specified volume. However, in the known unit steering stiffness of the actuator is insufficient because of the presence of the two gear transmission with mechanical volnoobrazovaniye which is in contact with a flexible wheel is not around the perimeter, and two symmetrical zones, resulting in gaps in the system volnoobrazovaniye - flexible wheel - hard wheel.To eliminate the above disadvantages of the block control surface actuators supplied with the first and second glasses, which are designed to accommodate mentioned supports bradey gear consists of a gear, having serially connected first and second cylindrical pairs, each of which contains a gear wheel, a ball screw transmission, consisting of a screw on the supports rotation and nuts and balls, designed to implement the interaction of the above-mentioned ball screw helical gears and bushings, and transfer to a rack and pinion gearing, consisting of Reiki gears mentioned kinematic chain made in the form of spatial Cam mechanism that allows to copy the mentioned rotation shaft of the steering wheel. The longitudinal axis of the shaft above the motor and the longitudinal axis of the movable links mentioned cylindrical gears, ball screw gear and Cam mechanism are parallel. Gear mentioned first pair of cylindrical gears rigidly mounted on the shaft above the motor, wheel-mentioned second pair of cylindrical gears rigidly mounted on the screw mentioned ball screw transmission, balls located between the inner surface of the nut and the surface of the screw mentioned ball screw transmission slots, made along a helical line, and the nut is installed inside plenium, designed to interact with the wheel, which is fixed on said steering shaft. The first mentioned glass is designed for rigid connection with the said fuselage, the second-mentioned glass is installed coaxially with the first mentioned glass so that the axis referred to the support roller is located outside the said sleeve. The said connection node consists of a threaded rod, which is designed to connect the aforementioned second glass fuselage, disk, earrings, plugs, and a spherical bearing, which is designed for fastening the said casing to said disk so that the earring is installed coaxially with the screw mentioned ballpoint transmission and is connected through the aforementioned spherical bearing with plug, which is located on said disk. Spike angular contact bearing referred to support rotation of the screw mentioned ball screw transmission is made as one piece with the screw, and the outer ring mentioned angular contact bearing mounted in said housing of the actuator. Mentioned Cam mechanism comprises a Cam and nut, and the Cam has the form of a shaft with slots on the outer surface, which are made by wee slots the shaft, which is connected to the position sensor mentioned steering via cross coupling. Nut mentioned Cam mechanism pivotally connected with the said sleeve. Nut mentioned ball screw transmission consists of two or more separate parts.The invention is illustrated by drawings. In Fig. 1 shows the layout of the control surface actuators, the cross section b - B in Fig. 2. In Fig. 2 - arrangement of control surface actuators, longitudinal section a-a in Fig. 1.Block control surface actuators (Fig. 1) consists of four identical actuators, each of which has a body 1. Each actuator includes a shaft 2 aerodynamic steering, mounted on legs of rotation 3 and 4, a motor 5, a sensor 6 provisions aerodynamic steering and gearbox. Mentioned the gearbox contains serially connected two-cylinder pairs 7 and 8, ball screw transmission, consisting of a screw 9 and nut 10, is made of two separate pieces, transfer to a rack and pinion gearing, which includes the rail 11 and the gear wheel 12. For connection of the sensor 6 with the shaft 2 used spatial Cam mechanism consisting of the Cam 13 and nuts 14. The Cam 13 has the form of a shaft with the slots the e transfer gear positioned that their longitudinal axis and the axis of the motor parallel and the transmission are connected as follows: on the shaft of the motor 5 is rigidly mounted cylindrical gear pair 7 and the cylindrical wheel pair 8 is rigidly fixed to the screw 9 ball screw transmission. Nut 10 is fixed inside the sleeve 16 made in the form of a cylindrical Cup, the outer surface of which is rigidly fixed to the rail 11. A gear wheel 12 mounted on the shaft 2. The supports 3 and 4 of the shaft 2 is placed inside the precast glass, consisting of the first glass 17 and the second glass 18. The first glass 17 is rigidly connected to the fuselage 19, the second glass 18 contains the axis 20 of the support roller 21. The support roller 21 and the gear wheel 12 to form a support sleeve 16, while their axes are eccentric. In addition, the spike 22 radial bearing supports rotation of the screw 9 is made in one piece with the screw 9, and the outer ring 23 of the above-mentioned bearing mounted in the housing 1. The sensor 6 is connected with the Cam 13 via cross coupling 24 and the nut 14 by means of the hinge 25 is connected to the sleeve 16. The housing 1 contains a ring 26 mounted coaxially with the screw 9. Earring 26 with a spherical bearing 27 serves to support the housing 1 relative to the fork 28, which is located aqueous attached by a nut 31 to the disk 29, and the other is connected by a threaded connection with a glass of 18 shaft bearing 2. Between the surface of the screw 9 and the inner surface of the nut 10 in the slots, made by helices are balls 32.Unit steering works as follows.When applying the control signal to the electric motor 5 of any of the four actuators it starts to rotate and transmits torque through two series-connected cylindrical pairs 7 and 8 of the screw 9. Nut 10 together with the sleeve 16 and the rail 11 performs translational motion and creates a torque on the toothed wheel 12 and rigidly United with him the shaft 2. The progressive movement of the sleeve 16 via the hinge 25 is transmitted to the nut 14. The translational motion of the nut 14 is converted into rotational motion of the Cam 13 via cross coupling 24 rotates the engine sensor 6. The step of the Cam 13 is selected so that the angular displacement of the engine sensor 6 corresponds to the angular movement of the shaft 2.Use the gear actuator unit control surface actuators ball screw transmission and transfer to a rack and pinion gearing, deployed and executed as specified in the invention method enables the led is th block steering rods 30 are threaded, one end rigidly attached to the disk 29, mounted in the fuselage 19, and the other is connected by a threaded connection with the second Cup 18 shaft bearing 2 aerodynamic steering, and the connection support each actuator through a spherical bearing 27 with a fork 28 of the above-mentioned disk 29 increase the rigidity of the housing 1 of the actuator to the fuselage 19. In addition, side-by-side longitudinal axes of the cylindrical and ball screw gear reducer, spatial Cam mechanism and the electric motor 5 allows you to save the co measurement of building height actuators with the diameter of the selected motor 5, that is, provides the possibility of placing a block of steering actuators in the volume, which is limited to the inner cylindrical surface of the fuselage 19 aircraft and coaxially located outer surface of gazivoda jet engine mentioned aircraft. 1. Block control surface actuators of the aircraft, intended for placement between the inner surface of the fuselage of the aircraft and coaxially located outer surface of gazivoda jet dvigatel through a connection node, shaft aerodynamic steering, which is mounted on supports rotation, the electric motor, which shaft through the reduction gear is connected with said steering shaft, the position sensor mentioned steering, which is connected kinematic chain with said steering shaft, characterized in that each of the mentioned actuator is supplied with the first and second glasses, which are designed to accommodate the aforementioned pillars of rotation of the steering shaft, the sleeve and the supporting roller, designed to create a support mentioned sleeve, the said gear consists of a cylindrical gear having serially connected first and second cylindrical pairs, each of which contains the gear and wheel, ball transfer, consisting of a screw on the supports rotation, nuts and balls, designed to implement the interaction of the above-mentioned ball screw helical gears and bushings, and transfer to a rack and pinion gearing, consisting of a rack and gear mentioned kinematic chain made in the form of spatial Cam mechanism that allows to copy the mentioned rotation of the steering wheel, the longitudinal axis of the shaft above the motor and the longitudinal axis of the movable parts of the said cylindricus the first mentioned cylindrical pair of rigidly mounted on the shaft above the motor, wheel-mentioned second cylindrical pair is rigidly fixed to the screw mentioned ball screw transmission, balls located between the inner surface of the nut and the surface of the mentioned screw screw transmission slots, made along a helical line, and the nut is installed inside the said sleeve, the outer surface of which is rigidly fixed to the rail mentioned gear with the rack and pinion gearing, designed to interact with the wheel, which is fixed on said steering shaft, the first mentioned glass is designed for rigid connection with the said fuselage, the second-mentioned glass is installed coaxially with the first mentioned glass so that the axis referred to the support roller is located outside the said sleeve, the said connection node consists of a threaded rod, which is designed to connect the aforementioned second glass fuselage, disk, earrings, plugs, and a spherical bearing, which is designed for fastening the said casing to said disk so that the earring is installed coaxially with the screw mentioned ball screw transmission and is connected through the aforementioned spherical bearing with plug, which is located on upon the ka mentioned fulcrum of rotation of the screw mentioned ball screw transmission is made as one piece with the said screw, and the outer ring mentioned angular contact bearing mounted in said housing of the actuator.3. Block control surface actuators under item 1, characterized in that the said Cam mechanism comprises a Cam and nut, and the Cam has the form of a shaft with slots on the outer surface, which are made along a helical line, and the nut are spring-loaded balls that are designed to interact with the said slots of the shaft, which is connected to the position sensor mentioned steering via cross coupling.4. Block control surface actuators on p. 3, characterized in that the nut mentioned Cam mechanism pivotally connected with the said sleeve.5. Block control surface actuators under item 1, characterized in that the nut mentioned ballpoint transmission consists of two or more separate parts.
FIELD: aircraft manufacture; control of high-lift devices of wing (flaps, slats).
SUBSTANCE: electric motor (1) is mounted in one kinematic channel and is mechanically connected with sun gear wheel of planetary differential mechanism (6) provided at gearbox input; it is connected with electromechanical brake clutch (3) electrically connected in series with electric motor. Hydraulic motor (2) is mounted in other kinematic channel and is mechanically and hydraulically connected with hydromechanical brake (4) by means of control head; it is also linked with epicycle of planetary differential mechanism (6) via matching in-line gear train.
EFFECT: enhanced reliability; reduced mass of drive.
FIELD: engines and pumps.
SUBSTANCE: invention relates to aircraft engineering, particularly to drives of control aerodynamic surfaces. Assembly of control drives comprises actuators, each consisting of the housing, control surface shaft, high-speed motor and reduction gear. Additionally, each actuator comprises moving toothed rack and toothed quadrant in mesh with the latter. Toothed quadrant is fitted on the control surface shaft, while reduction gear is additionally furnished with ball-and-screw gear wherein sliding nut engages aforesaid rack, while sliding screw is fitted on the helical gear output shaft. Note here that the number of helical gear stages does not exceed two.
EFFECT: simplified design.
2 cl, 4 dwg
SUBSTANCE: invention relates to aircraft airframe units drives. Drive 2 comprises housing 4, primary engine 6 to create rotary motion, first reduction gear 10 mounted to convert rotary motion of primary engine 6 in rotary motion of output shaft with higher torque and low rpm. First reduction gear comprises casing 14 secured to rotate relative to drive housing 4 and second reduction gear 16 arranged to convert rotary motion of housing 14 of first reduction gear 10 in that with lower torque and higher rpm. Brake 20 is mounted to influence rotary motion from second reduction gear 16. With first reduction gear 10 unlocked in operation, applied brake inhibits displacement of first reduction gear case relative to housing 4 of drive 2. With first reduction gear 10 locked, brake 20 gets released to allow first reduction gear case 14 to revolve relative to drive housing 4. First reduction gear may revolve at output in the range of plus 180° to minus 180°. Besides, second engine may be used to drive second reduction gear. Proposed drive consists of the set of assembly units and parts and may be used for control over aircraft landing gear leg.
EFFECT: part may be moved with drive reduction gear locked.
17 cl, 3 dwg
SUBSTANCE: invention relates to aircraft engineering, particularly, rudder control electric drives. Proposed drive comprises linear control mechanisms arranged in single housing, common rudder opening mechanism and retracted rudder locking mechanism. Liner control mechanisms are engaged via reduction gearboxes with appropriate control surfaces fitted in rolling bearings. Output shaft of every reduction gearbox is engaged with rudder shaft via ball-and-screw gearing.
EFFECT: synchronous opening of rudders.
2 cl, 5 dwg
SUBSTANCE: invention relates to aircraft engineering. Aircraft wing has slat and slat support assy. Slat support lever is configured to disengage from case located far from wing leading edge when said slat is completely extended. Slat support assy comprises support lever with multiple bearing surfaces extending along its length and multiple cylindrical roller bearings. Said lever displaces to release the slat secured to one end of said bearing lever from aircraft wing leading edge. Every bearing stays in rolling contact with bearing surface to support slat bearing lever to guide it in slat release and retraction. Every bearing has rotary axis parallel with its bearing surface. Slat assy comprises two adjacent top bearing surfaces, both located at the angle to adjacent top bearing surface so that bearing related with every top bearing surface does no share common axis with bearing.
EFFECT: reduced weight.
15 cl, 7 dwg
SUBSTANCE: invention relates to aircraft engineering and concerns leading edge flap drives. Electromechanical drive contains two pull-out rails with teethed sectors, sectioned main shaft, split sleeves interconnecting main shaft sections, two electromechanical drives of main shaft sections with bodies fixed in wing main frame. Each body has following components installed in it: electric motor and electric motor rotor angular position sensor, double-stage harmonic reducing gear with rotation bodies with hollow output shaft having two cams with bearings and building rings of the first stage comprising wave former installed on them. The body contains stage separators. Separator of the first stage with placed in it rotation bodies interacting with waved surface of rigid wheel of the first stage on which wheel cams with bearings and building rings are installed. Separator of the second stage with placed in it rotation bodies interacting with building rings and waved surface of rigid wheel of the second stage. Rigid wheel of harmonic reducing gear first stage has hollow shaft, and wave former is placed on the hollow shaft. Separator of the second stage of harmonic reducing gear is fixed in body and is immovable. Rigid wheel of the second stage with waved surface is installed with possibility to rotate relative to body and has hollow output shaft. The main shaft the length of each section of which exceeds the length of one electromechanical drive is placed inside hollow rotor, the first stage rigid wheel hollow shaft and hollow output shaft of the second stage rigid wheel. Controlled uncoupler is installed between the main and hollow output shafts.
EFFECT: higher reliability of leading edge flap electromechanical drive.
5 cl, 4 dwg
SUBSTANCE: invention relates to means of controlling vehicles. Vehicle control unit comprises control system including handle unit containing control lever with first and second sections. To first section of lever first drive shaft is attached, and to second section of lever handle is attached at distance from first drive shaft. Lever with handle is arranged with possibility to turn about first rotational axis. Control unit includes wave gearbox containing flexible gear connected with second drive shaft, located at distance from first drive shaft. Second drive shaft can rotate about second axis together with rotation of flexible gear wheel. Lever mechanism is connected with first and second drive shafts so that rotation of second drive shaft around second axis turns lever mechanism around first and second axes of rotation, thus rotating first drive shaft around first axis.
EFFECT: possibility to provide direct, without controlled coupling, connection between engine, wave gearbox lever mechanism and control lever.
25 cl, 5 dwg
SUBSTANCE: flight control actuator drive (100) comprises first engine (10) for the first rotary inlet, second engine (12) for the second rotary inlet and device for speed summation (20) for connection of the first and second rotational inputs in one rotary output to control the actuator. Device for speed summation (20) comprises first and second circular input gears (22, 24), multiple pairs of planetary gears (30, 32). First planetary gear (30) is connected to first ring gear (22), second planetary gears (32) is connected to second ring gears (24), first and second planetary gears (30, 32) of each pair are connected to each other in mutual regulated mode. Carrier, which provides rotary output to control the actuator is connected to planetary gears.
EFFECT: possibility to backup drive, reduced weight and simplified design are obtained.
15 cl, 4 dwg
FIELD: rocketry, in particular, device for stabilization of aircraft winged missiles at the initial stage of independent flight.
SUBSTANCE: the body of the stabilizing device is made in the form of a convex cover sealing the nozzle of the missile solid-propellant acceleration engine, and the controls-in the form of four pairs of kinematically linked with one another aerodynamic control surfaces and jet vanes of the solid-propellant acceleration engine, each of them is positioned in the plane of installation of the aerodynamic control surface of the missile sustainer stage and linked with the drive of the mentioned control surface by means of control rods. The control mechanism of the stabilizing device control surfaces is made for separation of the links controlling the position of the device aerodynamic control surface, as well as for separation with the control rods from the sustainer stage control surface drive.
EFFECT: simplified structure and reduced overall dimensions of the stabilizing device, enhanced aerodynamic characteristics of the winged missile.
SUBSTANCE: invention relates to aircraft structural components and airfoils, particularly, to airfoils design for compact aircraft stabilisation in the plane of trajectory and for control in ballistic flight. Compact aircraft comprises fuselage, airfoils and tail plane. Airfoils are mounted at fuselage at the center of gravity to turn about aircraft lengthwise axis. Said airfoils represent two wings secured to turn assembly and arranged in symmetry about aircraft lengthwise axis in different planes.
EFFECT: higher aircraft efficiency, use of airfoils for flight control.
FIELD: weapons and ammunition.
SUBSTANCE: invention relates to missile engineering, namely to controlled missiles. A controlled missile includes a housing with the main control elements symmetrically arranged on it - aerodynamic surfaces and rudders, as well as a wire duct. The latter is arranged along the housing in the incline of rudders. An aerodynamic surface is additionally installed on the housing, on the side opposite to the wire duct.
EFFECT: improvement of aerodynamics of missile flight and improvement of its target guidance accuracy.
2 cl, 1 dwg
SUBSTANCE: invention relates to supersonic rocket airfoil control devices. Proposed unit consists of the shaft fitted in the case to turn therein, airfoil rigidly fitted on said shaft, steering unit, rollers and separators rigidly interconnected and fitted in rocket body. Steering unit rod is articulated with lever. Circular cavity composed by groove of the shaft and conical rolling paths on said rings house rollers arranged so that every next roller is perpendicular to previous one. Separator is arranged between said rollers.
EFFECT: operation at notable aerodynamic loads.
SUBSTANCE: invention relates to aircraft and rocket engineering. Folding steering surface of airborne hitting means comprises the base composed of two symmetric halves secured by fasteners, folding support and tension spring fitted in said base.
EFFECT: higher reliability of unfolding.
FIELD: armaments and ammunition.
SUBSTANCE: device of missile stabilization contains controls in form of four pairs kinematically linked with each other, and pair of ribbon tie-rods tensioned by turnbuckle with rollers of aerodynamic and gas vanes with shafts having slot for bushing, ring groove with wire passing through the rollers, rocker pivotally connected with pair of ribbon tie-rods.
EFFECT: invention reduces device dimensions.
SUBSTANCE: rocket control actuator unit consists of an aerodynamic surface, a shaft connected to aerodynamic surface with the ability to rotate, a lever rigidly mounted on the shaft, an actuator pivotally connected to the lever and fixed in the missile body, where the shaft is mounted on rollers in separators and divided shroud, rigidly fixed in the shell of the rocket, and each subsequent roller is located perpendicular to the previous one. Wherein, the rotation mechanism is in the form of a double-row bearing, one row of which, located to the aerodynamic surface, consists of taper rollers placed in separators with thermal gap that meets the requirements for sealing the unit, and the second row, located to the lever, contains needle rollers having axial deflection freedom, 2-3 times greater than the end play of rollers first row. Each row of rollers is filled with a powder mixture of graphite with molybdenum disulphide.
EFFECT: creation of a simple reliable rocket control actuator unit operating at high aerodynamic loads, high ambient temperature, ensuring the requirements for actuator tightness.
SUBSTANCE: it contains a pair kinematically connected to each other with the help of a rocket mounted on the body and a control mechanism for the aerodynamic and gas rudders. The latter contains a base and a compensation mechanism, which is made in the form of two pairs of identical rods, pivotally connected to each other by means of a transition element. The first pair of rods is hingedly connected to the rods drawn from the aerodynamic handlebar by means of a rocking arm pivotally connected to the base. The second pair is hingedly connected to a rocker that is rigidly connected to the gas rudder. The lengths of the transition element and of both rockers are equal. The distance between rockers in the initial position is less than the sum of the rods length from the first pair and the rod from the second pair by the amount of compensated displacements. At the same time, one end of the base is rigidly fixed on the rocket body in the region of the aerodynamic handlebars, and the other end with the rocker is mounted with the possibility of longitudinal displacement.
EFFECT: it allows to use stabilization devices on rockets with larger distance between aerodynamic and gas rudders, reduce size and mass of the rocket, and reduce the cost of its production.
FIELD: weapon and ammunition.
SUBSTANCE: device for two-stage rocket stages separation is made in the form of a steering control mechanism mounted on the rocket body with a possibility of two links separation (at the time of rocket stages separation). One link is kinematically connected with the aerodynamic steering wheel shaft, which is placed on the main rocket stage. The other link is connected to the gas rudder, which is placed on the starting stage. The link, connected with the aerodynamic steering wheel shaft, contains a rocker, hingedly mounted on the main stage, at the ends of which two grooves are made. One groove is intended for placement of a finger, rigidly fixed on the lever of the aerodynamic handlebars steering wheel shaft. The other groove is intended for placement of a finger rigidly fixed to the rocker of the link connected to the gas rudder, mounted on the starting stage. At that, the rocker ends are pivotally connected to a pair of rods pivotally connected to the gas rudder rocker.
EFFECT: simplified design of the device for two-stage rocket stages separation with a possibility to disengage the links of the steering control mechanism.