RU2395428C1 - Aircraft landing gear front leg control device - Google Patents

Abstract

FIELD: transport. ^ SUBSTANCE: invention relates to aircraft engineering, particularly to aircraft landing gear front leg taxiing devices. Proposed device comprises interconnected handles arranged on the cab right and left, command transducers arranged under pedals and handle and linked therewith. Said device comprises also limit switches, centering spring cylinder linked with aforesaid handles and mechanism to center the shaft of command transducer arranged under the handle. Gear box, limit switches, centering spring cylinder of the handles, and mechanism to center the shaft of command transducer are arranged in one unit that has one input and two output elements. Note here that said input element represents a column rigidly engaged with gear box gear and handle. One output element that makes an extension of input element column is articulated with the handle on opposite side while second output element is coupled with command transducer shaft. Mechanism to center the shaft of command transducer, when in neutral position, represents two spring-loaded rockers and thrust arranged there between. Said thrust is mounted on gear box housing. Note also that articulation between handles in left and right sides represents a steel rope. ^ EFFECT: reduced weight and sizes, simple design and higher reliability. ^ 8 dwg

Description

The invention relates to the field of aviation, in particular to control systems for taxiing device of the front landing gear of the aircraft, and is intended to control the movement of the aircraft on take-off, landing and taxiing on the airfield.

A control system for the front landing gear of the aircraft is known (see the IL-86 airplane flight manual. - M .: Publishing House of the Design Bureau named after S.V. Ilyushin, 1976, section 10, pp. 5 and 6, Fig. 10 and 10- 2) containing steering wheels for controlling the aircraft with three-position switches for operating the steering control system, installed on the left and right sides of the handle cabin of the steering control system, connected via gears to each other by hard mechanical wiring, command sensors for the take-off and landing mode under the pedal For steering mode, associated with control handles, feedback sensors on the front support, connected to the rotary part of the support, gearboxes mentioned above for changing the gear ratio from handles to command sensor shafts for steering mode, centering spring cylinder, mechanically connected to the handles, for returning them and the sensor shafts for the steering mode to the neutral position, electronic control units, electrically connected to the sensors and electro-hydraulic units feeding idrozhidkost cavity in the cylinder device taxiway front support stops on the gear column and rigidly connected with the left crank pilot for restricting the rotation of the handle.

When using this system, the pilot needs to remember what position the three-position switch is in, in order to switch the system to taxiing, takeoff-landing or off if necessary. When transient processes of take-off, landing, taxiing are likely to be error-prone, which can lead to emergency situations, thereby reducing flight safety. In addition, the presence of two gearboxes, one under each handle, as well as a change in the gear ratio from the handles to the command sensor shafts for the steering mode in two places, in the gearboxes and the connection of the sensor shafts to the wiring between the handles, complicate the system, increase its weight and dimensions.

A control system for the front landing gear support of the aircraft is also known (see RF patent No. 2070140, class B64C 25/50), containing control wheels for the aircraft with on-off switches installed to turn off the system and turn on the take-off and landing mode, installed on the right and to the left sides of the handle cabin, through gearboxes with rigid mechanical wiring connected to each other and with a centering spring cylinder that returns the handle to the neutral position, control pedals also kinematically connected to each other and to the input GOVERNMENTAL shafts command sensors to "takeoff and landing" mode, command mode sensors for "steering" gearboxes for changing the transmission ratio from the handles to the shafts command sensors for the mode "taxiing". The system also includes a cam mechanism for switching between takeoff and landing - taxiing and vice versa kinematically connected to the column of one of the control levers and having limit switches connected via two parallel switching circuits with switches mounted on the helms of the left and right pilots, and the mechanism for connecting command sensors for the steering mode, kinematically connected with the column of the other control handle, which is also connected to the centering mechanism of the shaft of the command sensors for the mode "Steering", containing an additional centering spring cylinder mounted pivotally on the column and connected to the additional centering spring cylinder, a rocking chair with a gear sector, rods connected to the gear sector and levers on the sensor shafts, electronic control units, electrically connected to the sensors and electro-hydraulic units that supply hydraulic fluid in the cavity of the cylinders of the taxiing device of the front support.

The reasons that impede the achievement of the technical result indicated below include the fact that the on-board controls have two-position switches for turning the control system of the taxiing device into takeoff and landing mode, after the plane lands and turning off the control system of the steering device after takeoff, so that the wheels did not turn in the compartments of the chassis when moving the pedals. The pilot must remember what state the system is in and turn off and turn on the system during takeoff and landing, which reduces flight safety.

Placement of a block of limit switches, a cam mechanism to control their operation, a gearbox for changing the gear ratio from the handles to the shafts of the command sensors of the steering mode, a centering spring cylinder to return the handles to the neutral position, an additional spring cylinder to center the shafts of the sensors, separately located units, kinematically interconnected, requires a lot of space on the plane to place them, increases the weight of the system, complicates their installation, adjustment and maintenance in operation, reduces the reliability of the system.

The installation of stops restricting the rotation of the handles on only one side of the gear leads to the loading of all wiring from the right pilot to the left pilot, by the effort of the right pilot when the handle is rotated by the right pilot to the extreme position, which leads to an increase in the weight of the wiring.

The objective of the invention is to remedy these disadvantages, namely reducing the size and weight of the device, simplifying the design, improving convenience and reducing the time of service of the device, increasing the reliability of its operation.

This object is achieved by the fact that in the control device for the front landing gear of the aircraft, containing handles mounted on the right and left sides, mechanically connected to each other, command sensors under the pedals and the handle, mechanically connected to the pedals and handles, limit switches, centering spring cylinder, mechanically connected with the handles, as well as the centering mechanism of the command sensor shaft under the handle, according to the invention, a gearbox, limit switches, a centering spring cylinder p the cabin, the centering shaft of the command sensor shaft under the handle are placed in one block with one input and two output elements, while the input element, made in the form of a column, is rigidly connected to the gear gear and the handle, one output element, which is a continuation of the input element column, kinematically connected with the handle on the other side, the second output element is connected to the shaft of the command sensor, and the centering mechanism of the shaft of the command sensor in the neutral position is made in the form of two springs GOVERNMENTAL rocking and additional abutment therebetween, mounted on the gear case, moreover, the kinematic connection between the levers on the left and right sides is made as a wire rope.

Installation of units in a single unit requires less space for their placement, reduces the total weight of the control device for the front landing gear, allows the installation of units in the unit outside the aircraft in the production room, thereby increasing the ease of installation, build quality, and reliability. The finished unit is installed on the plane.

The invention is illustrated by drawings:

figure 1 shows a view against flight on the installation of the control handle on the port side;

figure 2 is a view a of figure 1;

figure 3 is a section bB of figure 2;

figure 4 is a section bb In figure 3;

figure 5 is a section EE of figure 3;

figure 6 - installation of the control handle on the starboard side (side view);

Fig.7 is a view D of Fig.6;

on Fig is a control block diagram of the front landing gear of the aircraft.

The control device for the front landing gear support of the aircraft (see Figs. 1-8) contains a cylindrical gear 1 (Fig. 1) located on the port side 2 (Fig. 1) of the cockpit; the input shaft of the gearbox 1 (Fig. 1) is made in the form of a column 3 (FIGS. 1, 3) installed in the gear housing 4 (FIG. 3), a control handle 5 (FIG. 1) and a mode switching mechanism 6 (FIG. 3), consisting of a shutter 7 (FIG. .3) and limit switches 8 (figure 2) mounted on the cover of the gearbox 9 (figure 3). On the column 3 (Fig. 3), a gear 10 (Fig. 3) is installed in the middle part, which is in gearing with a wheel 11 (Fig. 3), made integral with the output shaft of the gearbox 12 (Fig. 3) installed in the housing gear 4 (figure 3) and connected to a leash 13 (figure 5) having a central cutout used to control the shaft 14 (figure 3) of the command sensor 15 (figure 3), through the two-arm lever 16 (figure 3) mounted on the shaft 14 (figure 3). The axis 17 (figure 3), mounted on the shoulder 18 (figure 3) of the lever 16 (figure 3), enters the Central cutout of the leash 13 (Figure 5) with the same clearance G (Figure 5) with the sides of the cutout, and on the shoulder 19 (Fig. 5) of the lever 16 (Fig. 3), a roller 20 (Fig. 5, 1) is fixed, with which the elements of the centering mechanism of the shaft of the command sensor, the rocker 21 (Fig. 5) and 22 (Fig. 5) interact mounted pivotally on an arm 23 (FIG. 5), mounted on a gear housing 4 (FIG. 3), and having a stop 24 (FIG. 5), mounted on an arm 23 (FIG. 5), and the second ends 25 (FIG. 5) and 26 (Fig. 5) of the rockers 21 (Fig. 5) and 22 (Fig. 5, 1) are connected to the springs 27 (5) and 28 (Figure 5) between them. In the lower part of column 3 (Fig. 1), a roller 29 (Fig. 1) is installed, which is connected by a cable wiring 30 (Figs. 1, 6) to the roller 31 (Fig. 6) on the starboard column 32 (Fig. 6) 35 (Fig.6). In the upper part of the column 32 (FIG. 6), the control handle 33 is fixed (FIG. 6), and the column 32 (FIG. 6) itself is pivotally mounted in the bracket 34 (FIG. 6) mounted on the floor on the starboard side 35 (FIG. 6) the cab, as well as the lower end of the column 3 (Fig. 1) is pivotally mounted in another bracket 34 (Fig. 1), mounted on the floor on the left side of the cab. On the other hand, the column 32 (Fig.6) is pivotally mounted in the bracket 36 (Fig.6), mounted on the structure of the starboard side 35 (Fig.6) of the cab, and has a stop 37 (Fig.7), restricting the rotation of the control handle 33 ( Fig.6) between the stops 38 (Fig.7) on the bracket 36 (Fig.7). In addition, on the shaft 12 (Fig. 3) with a bolt 39 (Fig. 3), a lever 40 (Figs. 3, 4) is mounted pivotally connected to the tip 41 (Fig. 4) of the centering spring cylinder 42 (Fig. 4) and the cylinder cover 42 (Fig. 4) is fixed to the gear housing 4 (Fig. 4).

The control block diagram of the front landing gear support of the aircraft contains a rotation control device 43 (Fig. 8), including control handles 5, 33 (Fig. 8), limit switches 8 (Fig. 8), a command sensor for the "Steering" mode 15 (Fig. 8), then the pedal 44 (Fig. 8) with command sensors for the Take-off and Land "45 (Fig. 8), feedback sensors 46 (Fig. 8) kinematically connected with the rotary part of the front support 47 ( Fig. 8), taxiing cylinders 48 (Fig. 8), a control unit 49 (Fig. 8), an electro-hydraulic control unit 50 (Fig. 8) according to the commands of the control unit, under yuschy taxiing hydraulic oil in the cylinders, on-off switch 51 (Figure 8) to enable the system to mode "takeoff-landing" and turn off the system, placed on a dashboard in the cockpit.

The operation of the device. The control system of the front landing gear on-off switch 51 is included in the take-off-landing mode. To control the aircraft when taxiing on the ground (runway), turn one of the control levers 5 or 33, while columns 3 and 32 are rotated. Together with column 3, the shutter 7 is rotated and turns on the contacts of the limit switches 8, which switch the system to the “Steering” mode, gear 10 is also rotated, which rotates the wheel 11 with the output shaft 12 and the leash 13 installed on it by gearing. When the leash 13 is rotated the gap G is selected, which is necessary to turn on the limit switches 8 and switch the system into “steering” mode, the leash 13 starts to move the axis 17, which rotates the lever 16 and the shaft 14 of the sensor 15 connected to the lever 16, electrically signal from it is fed to the control unit 49, which generates a command to control the electrohydraulic unit 50, supply hydraulic fluid to the hydraulic cylinders 48 taxiway front support device. The roller 20 mounted on the shoulder 19 of the lever 16 rotates the rocker 21 or 22 (depending on the direction of rotation of the handle) and stretches the springs 27 and 28 connected to them. Simultaneously with the rotation of the output shaft 12, the centering spring connected to it is turned on through the lever 40 cylinder 42, which serves to return the handles 5, 33 to the neutral position when removing the load from them. In this case, the return of the shaft 14 of the sensor 15 to the neutral position occurs due to the rotation by the roller 20 and the springs 27, 28 of the rockers 21 or 22 until the rockers 21 or 22 touch the stop 24. Simultaneously with the rotation of the control handle 3, the roller 29 is rotated and through the cable wiring 30 roller 31 together with a column 32 connected to it and a control handle 33. Limiters when turning the control handle 3 are the stops inside the centering spring cylinder 42.

When controlling the rotation of the wheels of the strut of the front support from the handle 33 through the column 32 and the roller 31 fixed to it by cable wiring 30, the rotation is transmitted to the roller 29 and the column 3 and then the rotation control is carried out in the same way as from the handle 5. When turning the handle 33 to the extreme positions the emphasis 37 reaches the emphasis 38 in the bracket 36, thereby protecting the cable wiring from excessive effort during operation of the right pilot.

When the control handle 5 is turned left and right by a full angle limited by the stops in the centering spring cylinder 42, gaps remain between the stop 37 and the stops 38 on the bracket 36, so that the cable wiring is not loaded from the excess effort of the left pilot.

Claims (1)

A control device for the front landing gear of the aircraft, comprising handles mounted on the right and left sides of the cockpit, mechanically connected to each other, command sensors under the pedals and the handle, mechanically connected to the pedals and handles, limit switches, a centering spring cylinder mechanically connected to the handles, and a mechanism for centering the shaft of the command sensor under the handle, characterized in that the gearbox, limit switches, centering spring cylinder of the handles, the centering mechanism of the shaft of the command of the sensor under the handle are placed in one block with one input and two output elements, while the input element is made in the form of a column rigidly connected to the gear of the gearbox and the handle, one output element, which is a continuation of the input element column, is kinematically connected to the handle in another way board, the second output element is connected to the shaft of the command sensor, and the centering mechanism of the shaft of the command sensor in the neutral position is made in the form of two spring-loaded rockers and a stop between them, installed on the gear case, in addition, the kinematic connection between the handles on the left and right sides is made in the form of cable wires.

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