Aircraft landing gear with folding brace stabiliser release

FIELD: transport.

SUBSTANCE: aircraft landing gear comprises leg 1 pivoted to aircraft, folding brace 10 with two levers 11, 12, and brace stabiliser 20 in straight position. Said stabiliser 20 comprises two rods 21, 22 pivoted together and telescopic release 30 (release drive), for example, simple-action hydraulic cylinder. End 32 of release drive rod 31 is coupled with one of said rods 22. Rod 22 has arc-like slot 26 to receive rod 31. End of release drive rod 31 makes free moves in said arc-like slot without obstructing displacement of rod 22 outside of zigzag line position.

EFFECT: simplified release and compact design.

2 cl, 3 dwg

The technical field to which the invention relates.

The invention relates to take-off and landing gear of the aircraft, in particular to the unlocking means of stabilizing the folding strut of the chassis.

The level of technology

Many retractable landing gear is held in released position by a folding brace comprising two pivotally interconnected lever held in a substantially straight position by means of stabilization. One of the levers pivotally connected with the rack of the chassis, and the other pivotally connected with aircraft. The knee levers held in the straight position, form a rigid structure, locking the landing gear in the extended position.

Typically, the means for stabilizing includes two pivotally connected between a terminal to which the return spring force acts, keeping them in the straight position, in which they stabilize in the straight position the arms of the strut. The drive unlocking allows to disturb the alignment of the line rods stabilization funds, which leads to the violation of the linearity of the lever lock, allowing you to lift the chassis by means of the lifting drive, acting, for example, directly on the rack chassis.

You know the run of the drive unlock telescopic, to the verge on the one hand is connected with a rack chassis or with one of the levers of the lock, but on the other hand, is connected with one of the rods means of stabilization. During the release of the chassis when it is removed from the position in the released telescopic actuator unlock in normal circumstances can freely be lengthened or shortened as much as allow relative movement of the two parts, with which it is connected.

When folding the chassis must be powered telescopic actuator unlock so that it caused the violation of the straightness of the rods means of stabilization. Then in effect the lifting drive chassis, moving it in the retracted position. In this case, the knee levers and rods stabilization funds are given relative rotational movement, and they transmit the movement of the telescopic actuator unlock, sometimes it happens that the telescopic drive, if it remains enabled, prevents the lifting of the chassis.

The solution to this problem is immediately shut down telescopic actuator unlock as soon as he had completed his task, i.e. resulted in violation of the straightness of the rods means of stabilizing strut. However, this method requires more complex logic circuits lifting the chassis by installing sensors to detect violation of straightness rods that requires wiring on under ijnih parts of the chassis to transmit information from sensors in the computing device, which controls the logic of the rise.

Disclosure of inventions

The objective of the invention is to provide a technical solution that does not require shutdown of the telescopic means unlock during the climb phase of the chassis, but through which the telescopic means being enabled, cannot prevent the lifting of the chassis.

The problem is solved in the chassis, intended for installation on an aircraft with the ability to move between retracted and released positions, which contains:

- rack pivotally mounted on an aircraft to provide moving chassis between a retracted and released positions;

- folding brace with two pivotally connected levers, one of which is pivotally connected to the aircraft and the other to the chassis, with both levers are located essentially in a straight line, at least when the chassis is in a released position;

- means for stabilizing the knee in a straight position, comprising two pivotally connected by a rod, one of which is hinged to one of the levers of the knee, and the other pivotally connected to the chassis or to the aircraft, with both of the recoil force acting spring that holds them in the straight position, in the cat the rum they stabilize the knee levers essentially in a straight position;

- telescopic tool unlock, one end of which is connected to one of the rods, while the telescopic means is configured to selectively; enable for violations of the linearity of the location of the rods.

According to the invention the specified rod includes a groove, which includes the end of the telescopic means unlock, and the groove is shaped so that when the telescopic tool powered, end of the telescopic means unlock communicates with the bottom of the groove to bring the specified terminal in the broken line position, which it reaches when the telescopic tool comes in fully retracted position, and the groove allows the specified terminal to perform an arbitrary rotation beyond the position of the broken line.

Thus, during the lifting chassis actuate the telescopic tool unlock to break the straightness of the rods. In this case violated the straightness of the arm brace that allows you to lift the chassis by means of the drive of his recovery. During the movement created by the lifting drive, coupled with means for unlocking the rod can go beyond the provisions of the polyline. Such movement beyond a broken line occurs without participation of tools unlock, poidomani can not impede movement of the rod.

This embodiment avoids any opposition or resistance means unlocking the rotation of the rod beyond the position of the broken line and save simple logic control circuit means unlock, which may remain on during the entire lifting operation.

In addition, this eliminates an extra turn on the unlock tool, which is required in the well-known chassis to avoid interference with the movement of the rod beyond the broken line position by means of unlocking.

Thus, the actuator unlocking can be performed with only a small useful course that makes this drive is extremely compact.

The invention is illustrated by drawings.

Brief description of drawings:

1 schematically shows the chassis in a released position, and means to unlock and a rod with a circular groove in accordance with the present invention, side view;

figure 2 shows the chassis shown in figure 1, during the ascent when the tool unlock broke the straightness of the rods;

figure 3 - same as figure 2, but the chassis is the next stage of the ascent.

The implementation of the invention

Shown in figure 1 chassis contains the rack 1, pivotally connected to the aircraft with the ability povorotnoye the x-axis. Rack 1 includes a sliding rod (figure not shown), the end of which is mounted one or more wheels. As is known, the chassis is held in released position by means of brace 10, containing pivotally connected between a lower arm 11 and the upper arm 12. The lower lever 11 pivotally connected to the bar 1, and the upper arm 12 pivotally connected to the aircraft. As shown in this figure, the levers 11 and 12 of the strut is held essentially in the straight position: using the 20 stabilisation.

The tool 20 stabilization includes the first terminal 21 and the second rod 22, pivotally interconnected. The first rod 21 pivotally connected with the upper arm 12 of the strut, and the second rod 22 pivotally connected to the bar 1. With the first rod 21 connected to the spring 23, the retaining rods 21 and 22 shown in the figure the straight position, which is limited by the stops 24 and 25 located on each of the rods and in contact with each other under the action of the spring 23.

The rods 21 and 22 are held in the straight position, contribute to the stabilization of the levers 11 and 12 of the strut 10 is essentially in the straight position. Thus, the strut 10 forms a rigid structure, a locking rack 1 chassis from rotation around the X axis shown in the figure released position. All this world is but are shown to illustrate the context of the invention.

For lifting the chassis, you must break the straightness of the levers 11 and 12 of the strut 10. For this purpose between the bar 1 and the second terminal 22 has a telescopic actuator 30 unlock, in this case, the hydraulic cylinder simple steps that during his work creates a force tending to break the straightness of the location of the rods, overcoming the resistance of spring 23.

According to the invention, the end 32 of the rod 31 of the actuator 30 unlock, connected with the second rod 22, is included in the arc groove 26 made in the second rod 22 in the form of an arc of a circle with center on the Y-axis (in this case parallel to the X axis) swivel the second rod 22 with the stand 1.

As shown in figure 2, when the actuator 30 unlock powered in the direction of lowering of the rod 31, the end 32 of the rod 31 communicates with the bottom of the arc of the groove 26 and pulls the second rod 22 by rotating it around the axis of the swivel with counter 1, resulting in a broken straightness of the rods 21 and 22. When the actuator 30 unlock comes in fully retracted position, the second rod 22 is moved to the broken line position shown in figure 2. In this position, the straightness of the levers 11 and 12 of the strut 10 is disturbed sufficiently to chassis could rise under the action of the lifting drive (not shown), current is not orestano on rack 1, causing it to rotate around the x axis.

During lifting the chassis of the second rod 22 can be moved in an angular position beyond the broken line position, as shown in figure 3. This figure shows that the groove 26 provides movement of the second rod 22 beyond the broken line position (shown dotted), because the rod end of the actuator unlock moves freely in the arc groove without interfering with or creating resistance to movement of the second rod 22 beyond the provisions of the polyline.

Thus, the kinematics of lifting becomes extremely simple because it is sufficient to simultaneously operate the actuator unlocking and the lift drive chassis. The actuator 30 unlock pulls the second rod 22, thus deactivating the aligned rectilinear position, then the lifting drive, which becomes even more efficient at the expense of the straightness of the arm brace 10 continues its movement, lifting the chassis. During the lifting actuator 30 unlock remains enabled and is held in the retracted position. However, due to the presence of the groove 26, the actuator unlock does not offer resistance to movement of the second rod beyond the provisions of the polyline.

The invention is not limited to the described option for its implementation and covers any version within the volume, defined by the claims. In particular, although in this embodiment the groove is made arc, and the actuator remains fixed relative to the rack, when the end of the rod moves freely in the groove, it is possible to envisage other forms of notch, if only they allow the corresponding rod to move beyond the broken line position when the actuator is in the retracted position.

In addition, in this case describes a typical construction in which the actuator 30 and unlock the corresponding rod 22 pivotally connected with the rack chassis. There are also many other designs. The drive unlock can be connected, for example, with one of the levers of the knee and act on the rod, which is connected to the strut. In another known configuration, the actuator unlock can be connected to the aircraft and to act on the rod, which is hinged to the aircraft. The specialist will be able to apply the invention in such configurations.

Finally, this case presents the drive unlock, actuation of which causes the shortening to the position defined by the internal focus of the retracted, but for professionals it is clear that the invention can be used with the drive unlocked, enabling the which leads to its extension to the position defined internal focusing released position.

1. Chassis installed on an aircraft for movement between retracted and released positions, containing a rack (1), pivotally mounted on an aircraft with the ability to move the chassis between a retracted and released positions; folding strut (10) with two pivotally interconnected levers (11, 12), one (12) of which is pivotally connected to the aircraft, and the other (11) with the chassis, with both levers are, essentially, in the straight position, at least when the chassis is in a released position; means (20) stabilization of the knee in a straight position, comprising two pivotally connected by a rod (21, 22), one of which is hinged to the strut, and the other pivotally connected to the chassis or to the aircraft, with both rod return spring force acts, keeping them in the straight position, in which they stabilize the knee levers, essentially, in the straight position; telescopic means (30) unlock, one end (32) of which is connected to one of the rods, while the telescopic means is configured to selectively bring in action for violations of the linearity of the location of the rods, characterized in that FR is specified, one of the rods includes a groove, which includes the end of the telescopic means unlock, and the groove is made so that when the telescopic tool powered, end of the telescopic means unlock communicates with the bottom of the groove to bring the specified terminal in the broken line position, which it reaches when the telescopic tool comes in fully retracted position, and the groove allows the specified terminal to perform an arbitrary rotation beyond the position of the broken line.

2. Chassis according to claim 1, in which a groove is made in the form of an arc of a circle with centre on the axis (Y) of the hinge of the specified terminal.