RU2231127C1 - Adaptive load simulator for control levers of aircraft simulator - Google Patents

Abstract

FIELD: training equipment.

SUBSTANCE: proposed load simulator includes control lever, sensor showing displacement of control lever, computer complex, engine control system and loading unit. Lever is made in form of control stick provided with axle and dork. Control lever is additionally provided with hollow axle for fork made integral with this fork. Hollow axle of fork and axle of control stick are provided with wire guides made in two perpendicular planes. Segments of loading are connected with electric motor of loading unit.

EFFECT: increased speed of response; simplified construction.

4 dwg

Description

The invention relates to training devices and can be used in aircraft simulator or in other simulators of dynamic objects to reproduce efforts on the controls of a simulated object (aircraft).

A device is known for an adaptive loading simulator on the control levers of an aircraft flight simulator, reproducing various studied characteristics by means of loading cylinders interconnected through a variable ratio of rocking arms, between which a differential mechanism is installed, and adjustable rods are connected to the rods of the loading cylinders [1].

The disadvantage of this device is the low efficiency of teaching manual control of an object whose characteristics are simulated. This is due to the fact that the magnitude of the forces opposing the movement of the control handle is not related to the quality of control.

In addition, the use of an electro-hydraulic drive for reproducing forces on the controls significantly complicates and increases the cost of the simulator design.

Closest to the proposed is an adaptive loading simulator on the control levers of an aircraft flight simulator, comprising a control lever, for example, a control handle with an axis of rotation and a mounting fork, and a loading device.

The quality of control in the well-known simulator is ensured by the kinematic connection of the control lever with its displacement sensor, computer system, engine control system and boot device [2] - a prototype.

The disadvantage of this device is both the complexity of the design and its cost increase due to the use of an electro-hydraulic loading device for reproducing efforts on the controls. In addition, the use of a known device of hydraulic cylinders leads to a certain inertia of the loading simulator, since in a real manned object the electric control of the loading device is used.

The objective of the invention is to improve performance, simplify the design and reduce the cost of the adaptive loading simulator on the control levers of the flight simulator while maintaining the effectiveness of manual training.

The task is achieved by the fact that in the known adaptive loading simulator on the control levers of an aircraft simulator containing a control lever, for example, a control handle including the axis of rotation of the control handle with a fork mounted on it, the control lever is kinematically connected with its displacement sensor, a computing system, engine control system and loading device, it is supplemented by a hollow axis of rotation of the fork, made integral with the fork, while the hollow axis of rotation of the fork and the axis of rotation of the handle The controls are equipped with boot segments that are rigidly mounted on them with cable guides located in two perpendicular planes that are kinematically connected to the electric motors of the loading device, for example, by pitch and roll by means of cable wiring, while the cable wiring passes inside the hollow axis of rotation of the plug.

The use of cable wiring in the simulator to reproduce the efforts on the controls significantly simplifies and cheapens the design of the simulator, as well as improves its speed.

The rotation of the control lever in different spatial planes is ensured by the fact that the hollow axis of rotation of the fork, made integral with the fork, and the axis of rotation of the control handle are equipped with loading segments rigidly mounted on them with cable guides located in two perpendicular planes. At the same time, the efficiency of the loading mechanism simulator is ensured by the kinematic connection of the control lever with its displacement sensor, computer complex, and also the engine control system.

The movement of the control handle is transmitted to the hollow axis of rotation of the plug by cable wiring passing inside the hollow axis of rotation of the plug along the load segments guiding the cable wiring.

The execution of the plug at the same time with the hollow axis allows you to direct cable wiring inside the hollow axis to provide a mode of simulating loads on the pitch, which, in addition, reduces the size of the simulator boot device.

The proposed invention is illustrated by drawings.

Figure 1 presents an adaptive boot simulator on the control levers of an aircraft simulator;

figure 2 - control stick of the aircraft;

figure 3 - loading segments for pitch and roll;

figure 4 is a diagram of the kinematic connection of the control lever with a position sensor, a computer complex, a control system for the engine and loading motors.

A fundamentally adaptive load simulator on control levers, such as pedals or aircraft control sticks, is a circuit that converts signals generated by a position sensor into counteracting forces for pedals and / or aircraft control sticks 1 (Figs. 1, 4).

The control knob 1 is rigidly fixed in the cab 2 on the axis of rotation of the control knob 3 (see FIG. 2) with a fork 4 installed on it, integral with the hollow axis of rotation of the fork 5. Axis 5 is mounted in bearings 6. On the axis of rotation of the control knob 3 and the hollow axis of rotation of the fork 5 are rigidly mounted loading segments 7 and 8 in pitch and roll, while the segments 7 and 8 are located in two perpendicular planes (figure 3).

The axis of rotation of the control knob 3 with the loading segment in pitch 7 transfers loads from the electric motor 10 to the control knob 1 when it deviates in pitch from the neutral position forward or backward.

The hollow axis of rotation of the plug 5 with the load segment 8, respectively, transfers the load when the control knob 1 is tilted from the neutral position to the left or right.

At the same time, the loading segment by pitch 7 is kinematically connected by a wiring 9, rigidly fixed thereon, to an electric motor 10. In this case, the wiring 9 passes along the guide rollers 11 inside the hollow axis 5.

The roll loading segment 8 is kinematically connected by a cable wiring 12 to an electric motor 13. In this case, the wiring 12 passes along the guide rollers 14 and is rigidly attached to segment 8.

The device operates as follows.

By the force specified in accordance with the simulated flight mode and the deviation of the command lever from the neutral position, the device solves the load equation of the command lever 1 (pedals and / or aircraft control sticks) (see figure 4), the initial data for which come from position sensor 15.

Computing complex 16, solving the load equation, provides a signal to the engine control system 17, which controls the load motor 18, supplying control signals to it to create a moment that ensures the loading of the adaptive simulator mechanism in accordance with the simulated flight mode represented by data on flight conditions 19 ( flight altitude, speed, etc.) and the deviation of the command lever from the neutral position.

On the cable wiring 9, 12, the moment from the rotation of the electric motors 10, 13 is transmitted through the guide rollers 11, 14 and the hollow axis 5, the boot segments 7, 8 to the control handle 1, causing a corresponding force on it. As long as the control handle 1 is in the neutral position, there is no counteracting force preventing the movement of the handle 1. With an increase in the deflection angle, the opposing force increases in accordance with the loading characteristic and flight mode. The loading device generates a counteracting force for the control handle 1, depending on the magnitude of its movement and the given flight conditions of the simulated aircraft.

A prototype of the proposed device was manufactured and successfully tested at the training bench developed by AEROMASH CJSC, Minsk. The proposed device is used by CJSC “AEROMASH" in training equipment.

Sources of information

1. A.S. USSR No. 490156, G 09 B 9/08, dated 11.04.74, publ. bull. No. 40, 10.30.75.

2. RF Application No. 94013430, G 09 B 9/08, dated 04/18/94, publ. bull. No. 6, 02/27/96 - a prototype.

Claims (1)

An adaptive loading simulator on the control levers of an aircraft flight simulator, comprising a control lever, for example, a control handle including an axis of rotation of the control handle with a fork mounted on it, while the control lever is kinematically connected to its movement sensor, computer system, engine control system and loading device, characterized in that it is supplemented by a hollow axis of rotation of the fork, made integral with the fork, while the hollow axis of rotation of the fork and the axis of rotation of the control handle are provided with a rigid ment of them rope guides wiring load segments located in two perpendicular planes which are kinematically linked to the loading motor device, for example, pitch and roll by a tether wire, the cable runs inside the hollow plug passes the rotation axis.

Images