RU2647220C2 - Three-cordinate manual aircraft control station - Google Patents

Abstract

FIELD: airpower.

SUBSTANCE: three-coordinate manual control station contains a steering wheel, walking beams, rods, brackets. Wherein the station has an additional degree of freedom in the control of the roll, relative to the longitudinal axis of the aircraft (AC), which is provided by installing a thin-walled tube fixed in the hinges. Inside the tube, as far as the walking axis passes, the steering rods of the elevator and the rudder pass, which almost excludes the influence of roll channel on elevator and rudder.

EFFECT: independent simultaneous pitch, roll and yaw control, simple design.

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Description

The invention relates to aircraft, more specifically to manual control devices for actuating control surfaces of an aircraft, and can be applied when installing it between the dashboard and the pilot's seat to the ceiling of the cockpit, consisting of one person.

Known manual control posts as part of the helm and steering column have limited functionality, since they can only be used to control two control surfaces, namely the elevator, deflecting the steering column from itself and itself, the pitch angle of the aircraft changes, and the ailerons, turning the helm relative to the longitudinal axis passing through the upper part of the helm column (patents RU 2356793 C1, SU 999406 A1, SU 1376432 A1, RU 2420427 C2, US 2009/0321548 A1, US 2014/0014781 A1, etc.). The disadvantage of this manual control is that for the control of the yaw angle requires a complex foot control, namely the pedal.

Known manual control post having another degree of freedom, while the steering column has the ability to rotate relative to its own longitudinal axis perpendicular to the base (US 1798724 A, B64C 13/04, 03/31/1931, description pp. 1, 2, Fig. 1- 4, only 4 s.), Which provides longitudinal control of the aircraft and the rejection of foot control.

The closest to the claimed technical solution for the achieved technical result is a manual control post in which another degree of freedom is added to the helm structure, namely, the helm column together with the helm, which through a splined helm shaft mounted movably in a guide pipe passing through the cutout in the instrument panel, retains the possibility of rotation relative to its own longitudinal horizontal axis together with the helm, and the helm itself has the ability to separately rotate vatsya about an axis perpendicular to the longitudinal axis of the shaft (application for invention RF №2014132977). This device is adopted as a prototype of the invention.

The prototype of the control post provides control transfer to elevators, rudders and ailerons without the use of foot control (pedals).

The disadvantage of the prototype is that the movement of the rudders is made through complex technical devices in the form of telescopic rods, and the thrust of the rudder must also transmit rotation at different longitudinal positions of the movable and fixed sections. This solution is associated with the high complexity of manufacturing and cost of weight.

The objective and technical result of the invention is the device of a manual three-coordinate control post of an aircraft, which, having three degrees of freedom, provides independent independent control over all three channels, namely pitch, roll and yaw, and is notable for its simple design.

The problem is solved as follows: a three-coordinate post for manual control of the aircraft, containing a helm, rocking chairs, thrusts, brackets, is characterized in that the additional, relative to the longitudinal axis of the aircraft, helm control for roll control is ensured by installing a thin-walled pipe fixed in hinges, inside of which traction control rods and rudders pass as close as possible to the swing axis, which virtually eliminates the influence of the roll channel on elevators and directions.

The design lacks sliding friction pairs in the form of telescopic traction. The effect of the independence of the control channels is tested on the 3D model of the training glider, which is made in the SolidWorks program.

In FIG. 1 shows a General view of the three-coordinate control post of the aircraft as part of the training glider.

In FIG. 2 shows a separate control post, front view.

In FIG. 3 shows a separate control post, left view.

In FIG. 4 shows a separate control post, right view.

The three-coordinate manual control post has a housing 22 (Fig. 3), which is pivotally mounted in the fixed brackets 20 and 21 (Fig. 1), its longitudinal axis of swing 10 allows the control column 1 to move the mounting brackets of the ailerons of the drive ailerons 11 (Fig. 3) of the thrust (not shown conditionally), bracket 2 (Fig. 1) for fastening the rocker of the rudder drive 16 (Fig. 2), then connected to the rocker 5 (Fig. 1) rod 7, connected to the two-level rocker 12 (Fig. 4), to the upper arm 15 (Fig. 2) which is attached to the intermediate rod 23, and then the rod 19 of the steering wheel is directed and I; the rocker 4 (Fig. 3) of the elevator drive, inside of which the rod 14 of the rudder drive runs longitudinally and the rocker 5 of the rudder drive is pivotally mounted, the rocker 14 is pivotally mounted in the bracket 9, which is rigidly attached to the control unit housing 22, on the rocking lever 8 14 at the upper point, the intermediate rod 17 of the elevator is pivotally attached, which is connected to the rod 18, which is longitudinally mixed in the guide lunettes of the tail section.

The device operates as follows: when the steering column 1 is rotated relative to axis 3 (FIG. 1), the bracket 16 (FIG. 2), rod 14 (FIG. 3), bracket 5, rod 7 are moved, bracket 12 will rotate relative to axis 13 (FIG. 4) and turn the rocker 15 (Fig. 2), the rocker 15 moves the intermediate rod 23 (Fig. 1), which moves the rod 19 of the direct drive rudder. When the steering column 1 is deflected “by itself-away from you”, the rocking chair 4, rotating relative to the axis 6 (Fig. 3) in the bracket 9, will turn the lever 8, to the upper edge of which an intermediate link 17 is fixed, which moves the link 18 of the direct elevator. When the steering column is swinging about the axis 10 (Fig. 3), the tips 11 (Fig. 3) will move, to which the thrusts of the direct drive of the ailerons are attached. Rotations of the steering column relative to three axes provide control of the aircraft in any sequence and any combination of deviations without cross-action, since rotation of the housing 22 relative to axis 10 does not have a practical effect on the positions of the control rods 18 and 19 of the elevators and directions. Since the axis of the rods 18 and 19 extend along the axis of rotation of the aileron drive at a small distance according to FIG. 2 perturbations of displacements are second-order quantities of smallness, and are not taken into account in practical calculations.

The technical result of the use of a three-axis helm is the possibility of independent control over all three channels, namely, pitch, roll and yaw, and is characterized by the simplicity of design. Placing the helm in the upper part of the cockpit provides shorter rudder control paths for aircraft of the high-wing and biplane type; for low-wing type aircraft, the control post is located in the lower part of the cockpit.

Claims (1)

A three-coordinate station for manual control of the aircraft, containing a steering wheel, rocking chairs, thrusts, brackets, characterized in that the degree of freedom of the helm for roll control additional to the longitudinal axis of the aircraft is ensured by installing a thin-walled pipe fixed in the hinges, inside of which control rods pass as close as possible to the swing axis elevator and rudder, which virtually eliminates the influence of the roll channel on elevators and directions.

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