RU30705U1 - Executive mechanism for automatic aircraft control - Google Patents

Description

Actuator for automatic control system

The field of technology.

The invention relates to the field of aviation, more specifically, to an aircraft control system and can be used in the construction of an automatic alphanumeric system for moving control surfaces of an aircraft or a cruise missile using electrical control signals.

The prior art.

It is known that the actuator of an automatic control system (ACS) usually includes:

-steering autopilot car;

hydraulic booster (booster);

steering wheel.

The output rods of autopilot steering vehicles and self-propelled guns are connected via a power booster (booster) to the aircraft control wiring, which in turn is connected to the corresponding steering wheel. In this case, the deviation of the output rod of the booster leads to a deviation of the steering wheel. Such a design of an autopilot performing device (ACS) is widely used on airplanes and is described in detail in the literature. (See, for example: 1). "M.N. Shulzhenko. “Aircraft construction. Moscow “Engineering. 1971. p. 254 - 263.2). G.I. Zhytomyr. “Aircraft construction. Moscow “Engineering. 1991. p. 347 - 348. 3). Glagolev A.A., Goldinov M.Ya., Grigorenko S.M. “Aircraft construction. Moscow “Engineering. 1975. p. 269 277).

Closest to the utility model is the design of an aircraft control system with a servo wheel (rudder trimmer), in which “the pilot does not directly control the rudders or ailerons, but

 Hill shit "7- i

Class F 15 B.

by plane.

servo or servo compensators that are part of the steering wheel or aileron.

If you make the steering wheel freely rotatable on the axis of rotation and control the servo compensator, the steering wheel will always strive to turn itself in the opposite direction to the deviation of the servo compensator, until the moments of equality come .... "... Application. servo-control reduces the load on the pilot's control levers by 2–3 times, despite the fact that the coefficient of pivoting moment of the servo wheel relative to its axis of rotation due to the lack of axial and aerodynamic compensation is greater than the pivoting moment of the elevator.

This allows you to apply manual control of the aircraft at high subsonic flight speeds (S. M. Eger. "Design of passenger jets. Moscow" Engineering. 1964. P. 178, 179).

The above absence of axial and aerodynamic compensation of the servo wheel (trimmer) is explained by the fact that a possible overcompensation of the trimmer will lead to its throw with the throw of the control lever connected to it, i.e. to loss of controllability and disaster. The reduction of loads on the control levers (by 2–3 times) provided with this design does not allow the use of low-power autopilot steering cars without boosters in the executive mechanisms of automatic aircraft control systems. In such a control system, the autopilot actuator (ACS) is installed in close proximity to the steering wheel, i.e. in keel, wing or stabilizer. The executive mechanism of the autopilot (ACS) in this case includes the steering gear of the autopilot and the hydraulic booster (booster), which requires a hydraulic system. The use of steering units, in which an electric motor, a pump, control devices (i.e. a mini hydraulic system) and a booster with a steering gear of an autopilot are assembled in one mechanism do not change the essence of the matter - executive

Autopilot mechanism (ACS) is included in the wiring of the aircraft control system and is installed in the fixed part of the aircraft structure. All this makes the control system rather complicated and heavy. The reliability of such a system is reduced due to the presence of a hydraulic system and a booster (power steering). In addition, the large dimensions of the booster with the steering machine sometimes make it impossible to install self-propelled guns on an airplane during its modernization, since the self-propelled guns must be installed near the steering wheel, i.e. in the wing, elevator or keel, where free volumes are usually absent. The difficulties are compounded by the need to lay hydraulic pipelines from pumps, which are usually installed on engines, to boosters.

The essence of the utility model.

The objective of the invention is the creation of such an executive mechanism of autopilot (ACS), which would provide control of an airplane or a cruise missile without the use of a hydraulic system and a booster, which would provide a reduction in weight, increase reliability, deployment; use of this mechanism on an airplane without using; use of internal volumes stabilizer or keel.

The task is achieved by the fact that in the executive mechanism of the automatic control system of the aircraft I turn on; eat the steering wheel (altitude, direction or aileron), steering trimmer, autopilot steering machine, autopilot steering machine pivotally hinged on the steering wheel and connected to the steering trimmer pivotally with its output rod on the trimmer of the steering wheel bracket. Wires from the autopilot calculator (ACS) to the steering machine are routed inside the aircraft structure. When conducting wires to turn 1; ayush; to him, the steering wheel, you can avoid current-collecting devices and introducing wires to the outer surface of the steering wheel by laying the wires rolled into the tube (like wires are rolled to the telephone tube) inside the hollow axis of the wheel; the steering axle (hinge axis).

This design of the actuator of the self-propelled guns allows you to control an airplane or a cruise missile without the use of a hydraulic system and a booster, which ensures weight reduction, increased reliability, placement of this mechanism on an airplane without the use of internal volumes of the wing, stabilizer or keel.

The list of figures in the drawings.

The utility model is illustrated by drawings, which:

FIG. 1 shows a diagram of an actuator of an automatic control system with an autopilot steering machine placed on a steering wheel.

FIG. 2 shows a diagram of an actuator of an automatic control system with the placement of an autopilot steering machine inside the steering wheel.

FIG. 3 shows a diagram of the actuator of the automatic control system with minimal modifications to the steering structure during its modernization.

In FIG. 1, 2 and 3 are indicated:

1-Bearing surface of the aircraft (crash, stabilizer, keel).

2-Wheel (aileron, elevator, rudder).

3-Trimmer RU.LYA (servo).

4-steering autopilot car (RM).

5-output pin RM.

6-hinged connection of the PM output bar and trimmer.

7-swivel PM and steering wheel.

8 Fairing RM.

9-crochet trimmer.

Information confirming the possibility of implementation

The executive mechanism of the aircraft automatic control system consists of a steering wheel (pos. 2 in Figs. 1 and 2), equipped with 1 bracket (pos. 7 in Figs. 1 and 2) for hinged mounting of the autopilot steering gear (pos. 4), and a steering trimmer (pos. .3) with an arm (pos. 6) for swiveling with the output rod (pos. 5) of the autopilot steering machine (ACS). The autopilot steering machine is equipped with a fairing (pos. 8) to reduce the turbulence of the flow in the area of RU.11Ya and the trimmer. The steering wheel is hung on the bearing surface (stabilizer, keel or roof, - item 1 in Fig. 1 and 2) as usual. The wires rolled into the tube (from the autopilot computing device to the steering machine) are laid inside the hollow axis of rotation (hinge axis) of the steering wheel.

The autopilot steering machine may be mounted on the steering wheel from the outside, as shown in FIG. 1, or mounted inside the steering wheel, as shown in FIG. 2.

The device operates as follows.

The control electric signal is received from the control stick or autopilot (ACS) to the steering machine, which leads to a change in the length of the output rod and rotation of the steering trimmer. Deviation of the rudder trimmer (servo-steering) leads, if there is a sufficient velocity head, to a change in the lifting force on the trimmer and, therefore, to the rudder turning under the influence of this force to

as long as the moment from the action of the trimmer relative to the axis of rotation of the steering wheel does not become equal to the moment from the action of the forces of the steering wheel, i.e. to a new equilibrium (steering position). Thus, the position of the output shaft of the steering machine uniquely determines the position of the steering wheel of the aircraft. Servo wheels, trim tabs and steering cars of autopilots come up quickly and have long been used on airplanes. For example, a serial steering car of an autopilot RAU-107P, an invention.

the overcoming force at the output rod of up to 15 kgf will provide control of a trimmer of size 70 x 700 mm to an instrument speed of 1100 km / h on a subcritical number of M flights. The calculation shows that if the trimmer’s area is 4% of the rudder’s area, the trimmer’s deviation by 24 ° will provide a rudder deflection of 17 °, and if the trimmer’s area is 8% of the rudder’s area, the trimmer’s deviation of 17 ° will provide a rudder’s deviation of 25 °. The axis of rotation of the trimmer in the proposed actuator of the aircraft control system is selected in the focus of the steering wheel, i.e. with the possibility of overcompensation, which in such a scheme is not dangerous, since the aerodynamic loads from the trimmer are closed through the steering wheel of the autopilot to the steering wheel and are not transferred to the control wheels. Steering cars of autopilots withstand enormous loads on the output rod. For example, RAU-107R has a breaking force of 1600 kgf. on angular contact bearings. This is a purely electric car with a power of 25 watts. weighs 3.2 kg. In it, the electrical control signal by means of an electric motor, gear and worm gears, is converted into a longitudinal movement of the output rod.

You can use the specified actuator in the mode of the angular velocity damper and as a conventional trimmer. It is also possible to use ailerons in flap mode - this only requires a change in the control signal (control law).

The proposed autopilot actuator (ACS) can be implemented on newly created and existing aircraft and cruise missiles. When upgrading the aircraft, the proposed autopilot actuator (ACS) is installed in addition to the manual control system existing on the aircraft. In this case, the autopilot steering machine (pos. 4 in Fig. 1) is mounted on the steering wheel (pos. 2) by means of a swivel joint (pos.

7). If the airplane already has a trimmer, then a bracket (pos. 3) is mounted on it (pos. 3), to which the output rod of the autopilot steering machine is pivotally mounted (pos. 5). The existing trimmer control mechanism in this case is dismantled.

If there is no trimmer on the plane (which is almost unbelievable), or its area is insufficient, then an additional servo wheel is mounted on the steering wheel (trimmer - pos. З). At the same time, significant changes in the design of the existing steering wheel (except for hitching on it a trimmer and croshtein for the steering wheel of the autopilot) are not required (Fig. 3). When creating a new aircraft (which is possible with the modernization of the existing one), the steering wheel with the steering gear located in it is designed and rebuilt (Fig. 2).

The proposed autopilot actuator (ACS) can be installed on an airplane without the usual mechanical wiring of a control system. In this case, force or displacement sensors are installed on the control handle (lateral control handle, pedals) and, via a computing device, a control signal from the control handle (pedals) is supplied to the indicated actuating mechanism of the self-propelled guns.

In all cases, it is possible to install several sections of these actuators on each steering wheel to increase the reliability of the system as a whole. In addition, each steering wheel may consist of several independent sections.

Claims (1)

The executive mechanism of the aircraft automatic control system, including a steering wheel (altitude, direction or aileron) with a steering trimmer mounted on it, an autopilot steering machine, characterized in that the autopilot steering machine is pivotally mounted on the steering wheel and connected to the steering trimmer pivotally with its output rod by means of bracket steering trimmer.