Method of controlling means of locking thrust reversing electric system for turbomachine, computing device and turbomachine

FIELD: aircraft engineering.

SUBSTANCE: invention covers a method of controlling at least one means of locking a thrust reversing electric system for a turbomachine, herewith the method is implemented by means of a computing device prior to the aircraft take-off, and the method includes the following stages: sending a command for opening the locking means; checking the locking means opening; sending a command for closing the locking means.

EFFECT: reducing the risk of emergency during the landing phase.

9 cl, 2 dwg

 



 

Same patents:

FIELD: transport.

SUBSTANCE: invention relates to power engineering. Control system for aircraft driven by at least one engine installed in nacelle. Proposed system comprises: absolutely independent electronic control unit of jet engine operating conditions designed to control the conditions of at least one electrical device of the nacelle and to control said device directly. Note here that nacelle electric supply unit arranged outside aforesaid independent electronic control unit and designed to control the conditions of at least one electrical device of the nacelle. Invention covers also aircraft with above described control system.

EFFECT: decreased weight and sizes of said control system, lower servicing costs.

10 cl, 2 dwg

FIELD: transport.

SUBSTANCE: nacelle of an aircraft engine includes a sloping bonnet of a thrust reverser, a jet nozzle of a variable cross section and a device for bringing into action the bonnet and the nozzle. The jet nozzle is arranged in the downstream continued part of the bonnet and installed on the latter with a possibility of being shifted. The above devices include at least one power cylinder to actuate the bonnet of the thrust reverser, at least one drive gear installed in a turning manner on a fixed nacelle structure and at least one gear rack. The latter is attached to the nozzle and has a possibility of its actuation. The gear rack is engaged with the drive gear when the bonnet of the thrust reverser is in a forward thrust position and disengaged from the gear when the bonnet is in a reverse thrust position.

EFFECT: invention allows reducing the weight and simplifying the device actuating the jet nozzle and the thrust reverser bonnet.

7 cl, 18 dwg

FIELD: transport.

SUBSTANCE: system for actuation of at least one element of aircraft nacelle includes two drives, primary scheme of hydraulic or respectively electric energy generation and secondary scheme of electric or respectively hydraulic energy. The drives are kinematically interconnected. The primary scheme of hydraulic or respectively electric energy generation is intended to control one of the mentioned two drives, and the secondary scheme of electric or respectively hydraulic energy is intended to control the other drive.

EFFECT: invention permits to improve reliability of system for nacelle element actuation by means of providing heterogeneous redundancy in a system of simple structure.

7 cl, 2 dwg

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering. Torque restrictor comprises screw (101), nut fitted on screw, drive tube (105) rigidly coupled with said nut and means (109, 133) to actuate said screw. This constrictor is equipped with thrust (115, 119) to prevent revolution of said pipe (105) by friction caused by axial force brought by said screw (101) to said nut at its displacement. It allows rotation of said pipe (105) when the nut is shifted to contact with axial thrust of said screw to exceed preset threshold torque defined by said force.

EFFECT: higher efficiency.

7 cl, 4 dwg

Thrust reverser // 2538142

FIELD: motors and pumps.

SUBSTANCE: thrust reverser of the jet turbine engine nacelle contains deflecting elements and movable cowling including at least one flap installed on the movable cowling with the possibility of rotation. The movable cowling is made with possibility of movement from the closed position to opened position, and is equipped with drive-screw having slot in at least part of its length. The drive-screw slot is made with possibility of interaction with fixed guiding device of the nacelle to ensure the drive-screw rotation during translational movement of the movable cowling. The drive-screw is linked with movement transfer device of the flap drive system. The drive-screw slot is made spiral and has section of lost motion ensuring the drive-screw lost motion at the beginning of the movable cowling opening.

EFFECT: invention simplifies and reduces weight of the flap drive system of the thrust reverser.

20 cl, 14 dwg

FIELD: engines and pumps.

SUBSTANCE: invention relates to a system for control of multiple actuators, providing for movement of a mobile panel, which is a part of an aircraft nacelle, and such system comprises at least two engines, driving the specified actuators. The system also comprises two separate control units, besides, each unit is made so that control and supply to at least one engine is provided, which does not receive supply from the other control unit and is not under control of the other control unit. The invention also relates to a nacelle equipped with such control system.

EFFECT: provision for movement of a mobile panel with increased operational reliability.

18 cl, 6 dwg

FIELD: machine building.

SUBSTANCE: drive system comprises a ball-screw shaft, the first and second ball nuts interacting with it, a bearing and drive and interlocking mechanisms. The second ball nut is attached to the first unit able of displacement. The bearing is attached to the ball-screw shaft between the first and second ball nuts and is coupled with the second unit able of displacement. The drive mechanism is coupled with the first ball nut and can provide for its rotation. The interlocking mechanism can selectively connect the ball-screw shaft to the first ball nut. At the actuation of the thrust reversal mechanism the interlocking mechanism is withdrawn from the interaction position preventing the rotation of the first ball nut in relation to the ball-screw shaft. Afterwards the first ball nut is turned providing for the movement of the ball-screw shaft in respect to the first ball nut leading to the movement of a movable cowling coupled with the ball-screw shaft. At the actuation of the variable area fan nozzle the interlocking mechanism is brought into the interaction position providing for the connection of the first ball nut to the ball-screw shaft. Afterwards the first ball nut is turned together with the ball-screw shaft providing for the movement of the second ball nut in respect to the first ball nut leading to the movement of a movable cowling coupled with the second ball nut.

EFFECT: group of inventions allows for the decrease of engine weight due to the provision of a drive for independent cowlings by one drive system.

13 cl, 3 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed device comprises at least one cowl arranged to displace between closed and open positions and driven by at least one motor-controlled actuator. Every motor is connected to two separate power source. Note here that every motor represents a two-winding motor, every winding being connected to power supply other than that of another winding.

EFFECT: higher reliability.

9 cl, 3 dwg

FIELD: machine building.

SUBSTANCE: when controlling the drives of the movable cowl of a thrust reverser, the discrepancy of positions of adjacent drives is measured on a real time basis, and the speed profile of the respective drive or drives is changed in case the position discrepancy exceeds the certain specified limit. Should the measurements show that one of the drives is lagging behind the other ones, the said drive is accelerated or the other drives are decelerated. Should the measurements show that one of the drives is leaving the other ones behind, the said drive is decelerated or the other drives are accelerated.

EFFECT: invention provides for the prevention of jamming or damage of the movable cowl of the thrust reverser due to the prevention of asynchronous performance of adjacent drives responsible for its movement.

8 cl, 10 dwg

FIELD: engines and pumps.

SUBSTANCE: turbojet two nacelle control system comprises two power supply control units. Each of the latter can convert electric power. Every said unit comprises means to high-voltage power to electromechanical drive of at least one drive input for every power supply control unit. System incorporates also one control unit to supply control instructions to power supply control units that differs in design and separated from the latter. Said separate unit comprises at least one control input to receive data from engine controllers and at least two drive outputs to be connected to drive inputs of power supply control units.

EFFECT: simplified certification of controller.

14 cl, 2 dwg

FIELD: aircraft industry; turbojet engines; thrust reversers.

SUBSTANCE: proposed thrust reverser for turbojet engine has two flaps made for travel between open and closed positions of thrust reverser, each flap being controlled by electronic control unit 18a, 18b connected with computing fully reliable control device 20 and two locks 36a, 36b providing locking of flap to which it is connected. Each lock is made for operation by commands from two electronic control units 18a, 18b sent simultaneously.

EFFECT: improved safety owing to synchronization of control of primary locks.

5 cl, 2 dwg

FIELD: turbojet engines.

SUBSTANCE: proposed turbojet engine thrust reverser contains two doors 10a, 10b made for displacement between positions corresponding to open and closed positions of reverser by means of at least one control power cylinder 12, two electric 14a, 14b, each being coupled with at least on control power cylinder of each door. Each electric motor is controlled by electronic control unit 18a, 18b connected with fully-responsible electronic control computer 20. Two means for automatic control of each door travel by position setting orders are provided. Said automatic control means provide synchronous displacement of doors with due account of possible changes of forces acting onto thrust reverser and possible difference in force acting on each door.

EFFECT: improved reliability and safety of thrust reverser.

10 cl, 2 dwg

FIELD: turbojet engines.

SUBSTANCE: service panel 30 made for turning between at least two positions is coupled with each manual control box 28 of thrust reverser movable part 12. In first position, named working one, service panel prevents manual control of manual control box connected with panel permitting only its electric control. In second position, named service position, service panel permits manual control of manual control box connected with manual control panel prohibiting its electric control.

EFFECT: provision of higher safety when servicing thrust reverser doors owing to their mechanical interlocking.

8 cl, 9 dwg

FIELD: engineering industry.

SUBSTANCE: invention refers to the jet engine thrust reversers, containing at least one moving element (3), one lock device (7) with hook (8), communicating with gripping element (6) for the moving element holding up (3) in close mode, lock and closing double detection system (10), containing detector element (15) and permitting to assure, in particular, when signal occurred, that moving element (3) is in close mode and that device (7) is in lock mode. According to the invention closing double detection system and lock system of jet engine reverser moving element contains first device (16) of gripping element detection (6) and activation of second element (17) of hook (8) arched end detection (13).

EFFECT: exploitation reliability improvement.

12 cl, 11 dwg

FIELD: engines and pumps.

SUBSTANCE: invention refers to reversers of a jet engine rod. A lock (1) consists of tongue (3) and connecting component (4) where to control lever (15) is attached. The suggested lock is characterized with the following: slit (20) is cut in the control lever and the slit has gearing section, a narrowing section and end section. One more distinguishing feature is that a special catch pin designed so as to move against spring force has a recess with a cross section less than the cross section of the slit narrowing section. Due to that feature, when the said recess is located at a level with the slit as a result of the catch pin movement, the control lever may in turn travel from blocking position, when the catch pin is clamped at the end section, into a release position, when the slit and a catch pin are disintegrating. The device increases reliability of the lock by means of preventing of untimely traveling of movable parts of a reverser rod into a released position.

EFFECT: increasing reliability of the lock by means of preventing of untimely traveling of movable parts of a reverser rod into a released position.

10 cl, 11 dwg

FIELD: engines and pumps.

SUBSTANCE: invention relates to aircraft engineering, particularly to method of controlling aircraft gas turbine engine reverse thrust during aircraft roll-out. In compliance with proposed method, static pressure receivers are arranged on surfaces of outer and inner engines nacelles, their readings being compared to those of air pressure receiver (APR) during aircraft roll-out using thrust reverse. In case, there is no mismatch between aforesaid readings, inner engines thrust is kept invariable. In case, there is mismatch between readings of static pressure receivers arranged on the surface of nacelles of inner and outer engines, as well as between the readings of static pressure receivers fitted on outer engine nacelles surface and those of AVR, inner engines reverse thrust is reduced so that there are no aforesaid mismatches, i.e. Pst.out-Rst.inn≠0, Pst.out-Rst.AVR ≠0, where Pst.out, Pst.inn is static pressure on outer and inner engine nacelles, Pst.AVR is static pressure received from AVR. Proposed method comprises also comparing the readings of static pressure receivers arranged on outer and inner engine nacelles surfaces with AVR readings. Note that inner engine reverse thrust is varied during entire landing run of aircraft till thrust reverse outage.

EFFECT: improved landing performances and protection of engines against reverse jets and ingress of foreign matters.

FIELD: engines and pumps.

SUBSTANCE: invention refers to control method of opening or closing the turbo-jet thrust reverser by using at least one movable cover installed with possibility of being moved by means of at least one electric motor, which is characterised by the fact that there analysed is at least one parametre characterising the pressure in turbo-jet engine flow, and there performed is a sequence of operations, in which the operating parametres of electric motor are brought to conformity with the operating situation.

EFFECT: optimising the economy of mass owing to using electromechanical drives and increasing life time of thrust reverser.

17 cl, 7 dwg

FIELD: transport.

SUBSTANCE: invention relates electric control system to be mounted in aircraft turbojet engine nacelle. Proposed control system comprises set of electromechanical elements (8a, 8b, 12, 14), arranged in auxiliary actuators of turbojet engine and electronic control unit (15). The latter incorporates a set of control inputs (16-21) to be connected to control elements (37-40) and set of outputs (25-27) connected to aforesaid electromechanical elements arranged in auxiliary actuators of turbojet engine. Electronic control unit can convert every received instruction into operating sequence of at least one electromechanical operating element. Proposed nacelle comprises at least one movable fairing intended for servicing purposes at least one thrust reverser with at least one movable casing, and electric control system. Aforesaid fairing and movable casing are displaces by at least one electromechanical element (8a, 8b, 12, 14). Proposed control system allows centralising of control jobs and operating steps for actuators of servicing fairing casing.

EFFECT: simplified design.

11 cl, 3 dwg

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering, particularly to coupling between two elements of aircraft nacelle, namely thrust reverser. Coupling 1 between first nacelle element 2 and second nacelle element 3 that displace relative to each other comprises tongue 5 engaged with first nacelle element and can be engaged with retainer 4 of second structural element. Said tongue is arranged to counteract elastic return element 6 that acts to move the tongue into position of withdrawal. Besides there is stop 10 of second structural element that can retain said tongue in stressed state when second structural element stays nearby the first structural element.

EFFECT: ruling out of relative displacement of nacelle elements.

13 cl, 4 dwg

FIELD: engines and pumps.

SUBSTANCE: automatically the following serial stages are executed: - unfolding (E3) of previously connected aircraft thrust reversers; application (E5) of preset mode for engines; reduction (E6) of engines modes; - folding (E7) of aircraft thrust reversers.

EFFECT: improved reliability in control of aircraft on earth.

10 cl, 4 dwg

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