BG111127A - Method for designing aircraft simulators and simulator - Google Patents

Abstract

The invention relates to a method for the 3D design of aircraft and spacecraft simulators, which comprises the implementation of three steps that are structured as a sequence of actions for designingaircraft simulators. An aviation simulator which is intended for training pilots and is designed in accordance with the method comprises the following: a control unit (7) with monitors (21) mounted on a tabletop (1), wherein the tabletop (1) is attached to the ground by supports (13) pedals (2), which are adjusted by jacks (adjustors) (14), are attached to the tabletop (1) and are fixed by a bar(10), which is positioned in an X component (11) an aircraft control stick (3) a seat (4) a spindle (5) a support (a weight) (6) a post for a throttle lever (8) and a solid-fuel booster (9). In the PC is installed software for the aircraft. The field of vision corresponds to the type of craft. The aviation simulator is also suitable for a drive system using a device for producing g-force (24).

Description

Technical field

The invention relates to a method for the spatial design of simulators for manned aircraft and spacecraft intended for the training of pilots and astronauts and to an aviation simulator designed by this method, in particular a desktop simulator designed for the training of pilots.

BACKGROUND OF THE INVENTION

There are no known methods for the full spatial design of simulators for aircraft and spacecraft.

Aviation simulators are known, consisting of: at least one monitor connected to a computer displaying dashboards and ambient visualization, with some simulators also incorporating projectors in some of the dashboards and visualization. Standard joysticks, using a computer, realize the aircraft control lever, engine control lever (s) and pedals [1], [2], [3].

Other aviation simulators include monitors with depicted surroundings and a separate, real-world design of the entire cabin. The airplane control lever, engine control lever (s) and pedals correspond to the actual dimensions, location and effort applied to the actual aircraft [4], [5].

Known simulators have the following disadvantages: expensive overall construction due to high complexity, design time is too long, construction that does not fully correspond to the actual cabin of the aircraft.

SUMMARY OF THE INVENTION

The present invention is intended to solve the aforementioned disadvantages by facilitating the design of aircraft and spacecraft simulators by the application of the method. The proposed method is an opportunity for automated or semi-automated design, using specialized software and a sequence of pre-prescribed design stages. It creates constructive simulators for different types of aircraft and spacecraft.

The simulator is designed lightly at reduced labor cost and cost, and the overall environment (dashboards and visualization) is as close or completely identical to the actual aircraft or spacecraft as possible, providing that the simulated flights are stored, processed and stored. results.

The design of an aviation simulator according to the method allows any specialist in the field of simulators to design one, regardless of whether it has some type of aircraft or spacecraft

or a simulator, enough to have the output.

A method for the spatial design of aircraft and spacecraft has been developed, including:

1) Initial stage:

1.1) calculate semi-automated or automated, by computer and specialized software, the steering wheel deflections and forces transmitted to the control lever (s) and construct the deviation and speed balancing diagrams using known physical dependencies for the respective airplane or spacecraft with the following required data:

G - force applied to the control lever (s);

x _m is the relative coordinate of the position of the point of transition from laminar to turbulent boundary layer;

V - the maximum and minimum speed, which is divided into equal intervals, starting from V _m i _n to V _max ;

• f x _in - the distance measured from the cab by the displacement of the control lever (s) when deflecting the rudder.

Other additional data are also applicable.

1.2) calculate the semi-automatic or automated rudder deviation and the effort transmitted to the pedals (the deflection of the ailerons and the forces transmitted to the control lever (s)) and construct the balance diagrams of the deviations and forces using known physical dependencies for the aircraft or spacecraft concerned, subject to the following baseline data:

β - slip angle;

V is the maximum and minimum speed that is divided by

equal intervals ranging from V _min to V _max ;

_xn - measured from the cab distance when moving the pedals in deviation of the rudder;

x _el . - Measured distance when moving the control lever (s) when ailerons are deflected. When moving 20 °, the value is taken from the actual dimensions of the aircraft and spacecraft.

1.3) a comparison of the results of 1.1) and 1.2).

After performing the calculations and constructing the balancing diagrams of the samples and the calculations obtained for the control lever (s) and pedals, the following comparison is made and conclusions are drawn for further actions:

1.3.1) whether the deflection angles of the rudder are increased and whether the spring (s) acting on the tensile used in the specimen will stretch (t) more. The values obtained should be larger (in tension). If the condition is met, continue with the next action (below). If not returned in item 1.1), correcting the mistakes made and recalculating;

1.3.2) whether the deflection angles of the ailerons and the rudder are reduced and therefore that the tensile springs used in the specimens will stretch less. The values obtained should be smaller (in tension). If the condition set is fulfilled, continue with the action in item 1.4) (below). If not returned in item 1.2), correcting the errors and recalculating.

1.4) after the calculation process is completed, a real one is prepared

or a virtual layout. The model has dimensions that can be used for different aircraft and spacecraft, for vehicles with double occupancy in the cockpit, the distance between the seat area is doubled and the distance between the engine control lever (s) stand . Depending on the type of aircraft and spacecraft (with one and two seater positions in the cabin), the layout can only change in width. All other dimensions are retained in order to meet the Joint Aviation Requirements (JAR) requirements. The simulator layout is made in a decreasing scale. In order to reach the acceptable limits for flight and spacecraft simulators, a magnifying scale is used, and the resulting simulator is obtained at the M1: 1 scale according to the cab.

The calculations preserve the deviations and the efforts of the controls, shaping only the dimensions of the simulator (control lever (s), pedals, top, seat (s), axle, weight, test device, control lever stand). of the engine (s) and springs) on a larger scale. The standard dimensions (some of the dimensions of the pedals, of the control lever (s), seat (s), engine control lever (s), distances between some of them, etc.) measured by the cab are retained.

1.5) calculations of the springs, the samples of the control lever (s) and the pedals are made, assuming the springs of radius (diameter) R (D) of the permissible limit size to be constant [6].

In order to deflect the rudder and the ailerons when operating the control lever (s) and to deflect the rudder when controlling the pedals, cylindrical small spring springs are selected which will work in tension.

From the results obtained for the controls (lever (s) and pedals), stiffness is selected and the dimensions of each

* «♦ · * • · една една една една една one spring. The diameter adopted for structural reasons is initially taken on a magnifying scale as a constant for all springs applied to the control lever (s) and pedals, and then selected at M1: 1 scale, again being a constant for all springs applied to the control lever (s) and pedals.

1.6) combining the dimensions of three technological objects and creating a simulator:

1.6.1) the model of the simulator in descending scale;

1.6.2) on aircraft or spacecraft;

1.6.3) of computer equipment (monitors).

In order to perform the following steps from the steps and to obtain the W dimensions of the simulator, the dimensions of the cockpit in the cabin and the distance from the eyes of the pilot to the lantern or to the upper base of the cabin shall be ensured.

2) Work stage including:

2.1) after the necessary dimensions have been provided, we proceed to:

2.1.1) splitting the boards into a certain number of monitors;

2.1.2) are calculated by the coefficient formulas - R _n ; the total coefficients - R _zy , R _xy , R _xz ; the coefficient for determining the monitors (for selecting the monitors) - R _O 6mo; coefficients for reducing the dimensions of the simulator in the planes zy, xy, xz - R _czy , R _C xy, R _C x _Z :

CR _n = MM / TC

MM - the dimensions of the layout of the monitors

TC - the dimensions of the dashboard of an aircraft or spacecraft

R _Z y ^- R _nz + Rny

Rxy ^- Rnx + Rny for η - 1, 2, 3, 4

Rxz ~ Rnx + Rnz

Rnx, Rny, Rnz - coefficients equivalent to R _n with respect to the x-axis,

Y, z η - number of monitors, by location:

- main monitor (s)

- horizontal monitors

- vertical monitors

- monitor (s) positioned above the vertical and main monitors (s)

R-total (Rzy 4 · R _X y + R _xz ) / 3

_{R zy, R xy, R xz} - cumulative coefficients in the valleys O _zy, O _xy, O _xz

Kczy K _Z y / 2; K _CX y - K _xy / 2; Rcxz ^- Rxz '2

Rzy, Rxy, Rxz - total coefficients in the planes O _2y , O _xy , O _xz .

The values obtained for R _n ;, R _zy , R _xy , R _xz ; R _o6uio ; R _czy , R _cxy , R _cxz , used to draw the simulator in 2D and 3D space, transfer the project to space, define boundary dimensions, define monitors and assemble it. The results of the formulas are plotted in a table for each plane O _zy , O _hu , O _xz .

2.1.3) monitors are selected. It is preferable to use 3D LCD touch screen display, extremely thin monitors. Only 2D or 3D only can be taken. Due to the limited number of 3D monitors, they can be selected to be converted. This also allows the use of 3D glasses or the manufacture of a pilot's helmet glass such as that of 3D glasses.

Dashboard results are recorded in a table, recording the type of dashboard, monitor type, monitor number, width, height, diagonal and base.

When selecting monitors, the distance from the eyes of the pilot to the lantern or to the upper cab base shall be taken into account.

2.2) after the selection of the monitors, axonometric drawings are prepared in triplicate, with respect to the three coordinate planes O _xu , O _xz , O _yz . Apply to them the dimensions of the simulator on a magnifying scale and the boundary dimensions (the dimensions of item 2.1), divided by the coefficients R _czy , Rcxy, Rcxz in the planes of those on a magnifying scale.

2.3) From the dimensions obtained in a constructive way, the actual dimensions are selected. The actual dimensions are taken from the limit sizes by the allowable limits. They can be reduced below the limit, only if it is consistent with the structure and the cab. Spatial drawings are made in a type of isometry such as NE Isometric for

And the constituent parts. The entire simulator is then assembled virtually on a software product.

2.4) the simulator thus obtained is determined to be acceptable according to its actual dimensions in 3D space and prepared for drawing in 2D space for working drawings.

3) Final stage, including:

3.1) 3D plane springs are calculated with the necessary input data:

Pmin - minimum load applied to the control lever (s) and pedals;

I yell - the maximum load applied to the control lever (s) and pedals;

XB, HellHi - elevation coordinates, ailerons and rudder (controls);

G - modulus of angular deformation of spring steel С70;

Gdop - permissible tangential stress;

R (D) - reduced radius (diameter) of a flight simulator spacecraft in Ml: l. R (D) is a constant for all springs applied to flight and spacecraft simulators in step 3) at M1: 1 scale.

3.1.1) calculate the maximum torque M _cp ;

3.1.2) the maximum spring tension max f is calculated;

3.1.3) check the maximum tangential stress of the ottoman _x when dimensioning the cross section of the pure torsion of the ottoman _x <Gdop .:

3.1.3.1) the diameter of the cross section d is calculated;

3.1.3.2) calculate the number of active turns i;

3.1.3.3) record the result of the number of active turns i;

3.1.3.4) select springs.

3.1.4) calculate the minimum light aperture of 5 _m i _n ;

3.1.5) the initial light aperture δο is calculated;

3.1.6) the initial (free) length Lo is calculated;

3.1.7) calculate the length after loading max P L ₂ ;

3.1.8) calculate the length after loading min P Lj;

3.1.9) calculate the lengths of the tensile springs f] and

3.1.10) calculate the slope angle of the screw line a:

3.1.10.1) calculate the pitch of the springs h and record the dimensions d, D, δο, Lo and i of the springs.

3.1.11) calculate the length of screw line 1;

3.1.12) calculate the spring constant with;

3.1.13) the number of turns i is selected according to the distances obtained by the dimensions of the samples of the control lever (s) and the pedals;

3.1.14), it is repeated item 3.1.1), item 3.1.2), item 3.1.3) and

3.1.3.1);

3.1.15) for the selected values of the number of active turns i, the maximum spring tension max f is calculated again.

When transferring springs from 3D to 2D space, changes occur that affect the images in the working drawings.

For this purpose, the Oxyz coordinate system is used, for each plane a coefficient k _zy , k _xy , k _{xz is determined} . The coefficients k _zy , k _xy , k _xz are equivalent to c (k). For each maximal stretch of the springs max f, relative to the length after loading min P C and the number of turns i, the required space coefficient for all planes Ozy, Oxy, Oxz, taking into account the coefficients R _czy , R _C x _y , R _CX z from 2.1) and is recorded using the Oxyz coordinate system.

The springs are then calculated by taking the allowable value of the coefficient for the springs in space (k) multiplied by the coefficient with the maximum stretching of the spring. Ie (k) * max f.

3.1.16) is found from the maximum spring tension max f value of the coefficient for the springs in space:

3.1.16.1) the previous maximum stretches max f are divided by the coefficients for reducing the dimensions of the simulator in the plane zy, xy, xz, i.e., R _czy , R _cxy , Rcxzi

3.1.16.2) from item 3.1.15) take the newly obtained maximum springs of max f;

3.1.16.3) the newly obtained maximum stretches max f are multiplied by the coefficients for reducing the dimensions of the simulator in the plane zy, xy, xz, i.e. on R _C z _y , R _cxy , R _C x _Z ;

3.1.16.4) obtain coefficients for the springs in space (k) for each plane Ozy, Oxy, Oxz.

The arrangement of the springs determines in which plane the action is carried out and which coefficient will be used. The following additional calculations are made which determine (prove) the operation of the controls (control lever (s) and pedals), i. and the operation of the springs.

3.1.17) springs are selected;

3.1.18) the values of the minimum clear aperture of 6 _m j _n are taken

from item 3.1.4);

3.1.19) additional calculations are made of the initial bright aperture δο;

3.1.20) additional calculations are made at the initial (free) length Lo;

3.1.21) make additional calculations of the length after loading max P L ₂ according to the formula:

L ₂ = Lo + max f + (k) * max f

3.1.22) make additional calculations of the length after loading min P Li;

3.1.23) additional calculations of the lengths of the tensile springs fi and f _{2 are made} :

3.1.23.1) safj;

3.1.23.2) for f ₂ .

3.1.24) make additional calculations of the angle of inclination of the screw line a:

3.1.24.1) further calculations of the spring step h are made;

The dimensions of the springs are described as: d, D, δο, Lo, i.

3.1.25) additional calculations are made for the length of the screw line 1;

3.1.26) additional calculations of the spring constant with the formula:

c = max P / (max f + (k) * max f)

3.2) According to the calculations obtained, the springs are applied to the control lever (s) and pedals.

The aviation simulator shall be designed using the spatial design method of flight and spacecraft simulators and shall consist of at least one personal computer. Countertop that holds with supports inside and out. The supports are fixed to it and the floor with nuts and bolts. Only the lateral parts of the table where the seat passes are not supported by supports from the outside. It is fitted with monitors at a specified distance for reasons of distance in the cockpit of the aircraft. The dimensions of the whole structure are obtained according to the method of

spatial design of simulators.

The instrumentation in the cockpit and the environmental visualization are displayed on the monitors as follows:

1) The dashboard monitor includes all the instrumentation in the cockpit and the visualization of the surrounding area, i. the area where flights are made;

2) monitors displaying side panels (vertical and horizontal).

The pedals attached to the hob are adjustable. Adjustment is carried out with a raised (regulator), which moves them after pulling the control lever out of the cab. A profile is formed on the hob, where it is attached to the pedal lift (regulator), by placing a bar in article X and thus being held.

The control lever of the airplane through which the pedal axle passes shall be stopped by a part of that larger diameter axle which is fixedly fixed to the floor of the room. The seat is movable. It moves along the axis and is stopped by a mechanism or a nut. The axle is fixed to the raft at one end, and at the other end with a support (weight).

The airplane control lever, the engine control lever and the pedals are joysticks that are connected to the personal computer (s), with the airplane control lever taking the appropriate joystick and connecting to the pattern, and the engine control lever - the joystick is placed on the stand, and the pedals with the hoist (knob) are connected to the computer equipment.

In the desktop simulator, the noise emitted by the engine is obtained by an amplifier (speakers). The amplifiers are worn out or use so-called invisible speakers that are built into the monitors.

Field data and settings that are made are included in the program (s) in the program. The tester at the location of the printer is connected to the computer (connected to the monitor displaying the main display).

Explanations (description) of the attached figures

The invention will be better explained by the following description of several embodiments of the method for the spatial design of simulators for aircraft and spacecraft and aviation simulators according to the method and parts thereof, with reference to the accompanying figures, in which:

Figure 1 is an axonometric view of a layout obtained in step 2);

Figure 2 is a top plan view of Figure 1;

Figure 3 is an axonometric view of an aviation simulator;

Figure 4 is a basic view of a simulator according to Figure 3;

Figure 5 is a top plan view of a simulator according to Figure 3;

6 is a rear view of a simulator according to FIG. 3;

Figure 7 is a larger-scale axonometric view of a seat-stopping mechanism that can be used in place of the nut according to Figure 3;

8 is a larger-scale axonometric view of a special key used to unlock the seat restraint mechanism of FIG. 7;

Figure 9 is a diagram of a single-cabin simulator in accordance with Figure 3;

FIG. 10 is a diagram of a two-seat cabin simulator according to FIG. 9; FIG.

Figure 11 is an axonometric view of a single-seat simulator in a cab with a propulsion system and a congestion device;

• · · · Figure 12 is an axonometric view of a two-seater cabin simulator with a propulsion system and an overload device.

Examples of carrying out the invention

The method for the spatial design of flight and spacecraft simulators has been clarified using the following exemplary embodiments without limiting them:

Example # 1:

A method for the spatial design of spacecraft simulators has been developed. The method is as follows:

1) Initial stage:

For spacecraft, the method sequence is used, the first two actions being performed for spacecraft with the relevant necessary input data. Other additional data are also applicable.

1.3) a comparison of the results of 1.1) and 1.2).

After performing the calculations and constructing the balancing diagrams from the samples and from the calculations obtained for the control levers and pedals, the following comparison is made and conclusions are drawn for further actions:

1.3.1) whether the deflection angles of the controls are increased and whether the spring (s) acting on the tensile used in the specimen will stretch more. The values obtained should be larger (in tension). If the condition is met, continue with the next action (below). If not returned in item 1.1), correcting the mistakes made and recalculating;

1.3.2) whether the deflection angles of the controls decrease and therefore whether the tensile springs used in the specimens will stretch less. The values obtained should be smaller (in tension). If the condition is fulfilled, proceed with the action in item 1.4) (below). If not returned in item 1.2), correcting the errors and recalculating.

1.4) after the calculation process is completed, a real or virtual layout is prepared. The layout of the spacecraft is like that of a double seater cabin. The distance of the seating area doubles. The layout only gets modified in terms of width. All other dimensions are retained in order to meet the Joint Aviation Requirements (JAR) requirements. The simulator layout is made in a decreasing scale. In order to reach the acceptable limits for a spacecraft simulator, a magnifying scale is used and the simulator obtained after performing the following actions is obtained in a scale of M1: 1 according to the cab.

The calculations preserve the deviations and efforts of the controls, shaping only the dimensions of the simulator (control levers, pedals, countertop, seats, axle, weight, test unit, engine control arm and springs) in on a larger scale. The standard dimensions (some of the dimensions of the pedals, control levers, seats, engine control knob, distances between some of them, etc.) measured by the cab are retained.

1.5) calculations of the springs used in the samples of the control levers and pedals are taken, assuming the springs of radius (diameter) R (D) of the permissible limit size to be constant [6].

When operating the control levers and pedals, small, small-pitch cylindrical coil springs are selected for tension.

From the results obtained for the controls (control levers and pedals), stiffness is selected and the dimensions of each spring are formed. The diameter adopted for structural reasons is initially taken on a magnifying scale as a constant for all springs applied to the control levers and pedals, and then selected at M1: 1 scale, again the diameter being a constant for all springs applied control levers and pedals.

1.6) combining the dimensions of three technological objects and creating a simulator:

1.6.1) the model of the simulator in descending scale;

9

9

1.6.2) the spacecraft;

1.6.3) of computer equipment (monitors).

In order to carry out the following steps from the stages and to obtain the dimensions of the simulator, the dimensions of the cockpit in the cabin and the distance from the eyes of the cosmonaut and the upper base of the cosmic space are provided

apparatus.

2) Work stage including:

2.1) after the necessary dimensions have been provided, we proceed to:

2.1.1) splitting the boards into a certain number of monitors;

2.1.2) are calculated by the coefficient formulas - R _n ; the total coefficients - R _zy , R _xy , R _xz ; the coefficient for determining the monitors (for selecting the monitors) - Roomoi coefficients for reducing the size of the simulator in the planes zy, xy, xz - R _czy , R _CX y, Rcxz '·

R _n = MM / TC

MM - the dimensions of the layout of the monitors

TC - the dimensions of the spacecraft's panels

Rzy ~ Rnz + Rny

Rxy ~ Rnx + Rny for π - 1, 2, 3, 4

Rxz ~ Rnx * Rnz

Rnx, Rny, Rnz - coefficients equivalent to R _n with respect to the x-axis,

Y, ζ η - number of monitors, by location:

- main monitor (s)

- horizontal monitors

- vertical monitors

- monitor (s) positioned above the vertical and main monitors (s)

Rzy, Rxy, Rxz - total coefficients in the planes O _zy , O _xy , O _x2

Rzy, Rxy, Rxz - total coefficients in the planes O _zy , O _xy , O _xz .

The values obtained for R _n ;, R _zy , R _xy , R _xz ; R _o6ul o; R _czy , R _cxy , Rcxz, used to draw the simulator in 2D and 3D space, transfer the project into space, define boundary sizes, define monitors and assemble it. The results of the formulas are plotted in a table for each plane O _zy , O _hu , O _xz .

2.1.3) monitors are selected. It is preferable to use 3D LCD touch screen display, extremely thin monitors. Only 2D or 3D only can be taken. Due to the limited number of 3D monitors, they can be selected to be converted. This also allows the use of 3D glasses or the creation of a helmet glass on the cosmonaut's space suit, such as the 3D glasses.

Dashboard results are recorded in a table, recording the type of dashboard, monitor type, monitor number, width, height, diagonal and base.

When choosing monitors, the distance from the eyes of the astronaut to the upper base of the spacecraft is taken into account.

2.2) after the selection of the monitors, axonometric drawings are prepared in triplicate, with respect to the three coordinate planes O _xu , O _xz , O _yz . Apply to them the dimensions of the simulator on a magnifying scale and the boundary dimensions (the dimensions of item 2.1), separated by the coefficients R _czy , R _cxy , Rcxz in the planes of those on a magnifying scale.

2.3) From the dimensions obtained in a constructive way, the actual dimensions are selected. The actual dimensions are taken from the limit sizes by the allowable limits. They can be reduced below the limit, only if it is consistent with the structure and the cab. Spatial drawings are made in a type of isometry such as NE Isometric for components. The entire simulator is then assembled virtually on a software product.

2.4) the simulator thus obtained is determined to be acceptable according to its actual dimensions in 3D space and prepared for drawing in 2D space for working drawings.

3) Final stage, including:

3.1) 3D plane springs are calculated with the necessary input data:

· · · ·

Pmin - minimum load applied to control levers and pedals;

I yelled - maximum load applied to the control levers and pedals;

х „, х _ел ., х _н - coordinates of deviation of the control bodies;

G - modulus of angular deformation of spring steel С70;

τ _Λ0Π . - allowable tangential stress;

R (D) - reduced radius (diameter) of the spacecraft coil spring in Ml: l. R (D) is a constant for all springs applied to spacecraft simulators in step 3) on a scale of Ml: 1.

3.1.1) calculate the maximum torque M _cp ;

3.1.2) the maximum spring tension max f is calculated;

3.1.3) check the maximum tangential stress of an ottoman _x when dimensioning the cross section of a pure twist of an ottoman _x <

3.1.3.1) the diameter of the cross section d is calculated;

3.1.3.2) calculate the number of active turns i;

3.1.3.3) record the result of the number of active turns i;

3.1.3.4) select springs.

3.1.4) calculate the minimum clear aperture of 8 _m j _n ;

3.1.5) the initial light aperture δο is calculated;

3.1.6) the initial (free) length Lo is calculated;

3.1.7) calculate the length after loading max P L ₂ ;

3.1.8) calculate the length after loading min P Lj;

3.1.9) calculate the lengths of the tensile springs fj and

3.1.10) calculate the slope angle of the screw line a:

3.1.10.1) calculate the pitch of the springs h and record the dimensions d, D, δο, Lo and i of the springs.

3.1.11) calculate the length of screw line 1;

3.1.12) calculate the spring constant with;

• · ·

3.1.13) select the number of turns in accordance with the distances obtained by the dimensions of the samples of the control levers and the pedals;

3.1.14) repetition of item 3.1.1), item 3.1.2), item 3.1.3) and item 3.1.3.1) is performed;

3.1.15) for the selected values of the number of active turns i, the maximum spring tension max f is calculated again.

When transferring springs from 3D to 2D space, changes occur that affect the images in the working drawings.

For this purpose, the Oxyz coordinate system is used, for each plane a coefficient k _zy , k _xy , k _{xz is determined} . The coefficients k _zy , k _xy , k _xz are equivalent to c (k). For each maximum stretching of the springs max f, relative to the length after loading min P L] and the number of turns i, the required space coefficient for all planes Ozy, Oxy, Oxz, taking into account the coefficients R _czy , Rcxy, Rcxz of 2.1. and is recorded using the Oxyz coordinate system.

The springs are then calculated by taking the allowable value of the coefficient for the springs in space (k) multiplied by the coefficient with the maximum stretching of the spring. Ie (k) * max f.

3.1.16) is found from the maximum spring tension max f value of the coefficient for the springs in space:

3.1.16.1) the previous maximum stretches max f are divided by the coefficients for reducing the dimensions of the simulator in the plane zy, xy, xz, that is, R _czy , R _cxy , R _cxz ;

3.1.16.2) from item 3.1.15) take the newly obtained maximum springs of max f;

3.1.16.3) the newly obtained maximum stretches max f are multiplied by the coefficients for reducing the dimensions of the simulator in the plane zy, xy, xz, i.e. on R _czy , R _CX y, Rcxz;

3.1.16.4) obtain coefficients for the springs in space (k) for each plane Ozy, Oxy, Oxz.

The arrangement of the springs determines in which plane the action is carried out and which coefficient will be used. The following additional calculations are made to determine (prove) the operation of the controls (controls and pedals),

ie and the operation of the springs.

3.1.17) springs are selected;

3.1.18) the values of the minimum bright aperture 0 _m i _n are taken from item 3.1.4);

3.1.19) carry out se additional calculations on the initial one bright hole δο; 3.1.20) carry out se additional calculations on the initial (free) length Lo; 3.1.21) perform se additional calculations on the length

after loading max P b d by the formula:

L2 = Lo + max f + (k) * max f

3.1.22) make additional calculations of the length after loading min P Li;

3.1.23) additional calculations of the lengths of the tensile springs fi and f2 are performed:

3.1.23.1) for C; 3.1.23.2) for f ₂ .

3.1.24) make additional calculations of the angle of inclination of the screw line a:

3.1.24.1) additional calculations of the spring step h are made.

The dimensions of the springs are described as: d, D, δο, Lo, i.

3.1.25) additional calculations are made for the length of the screw line 1;

3.1.26) additional calculations of the spring constant with the formula:

c = max P / (max f + (k) * max f)

3.2) In accordance with the calculations obtained, the springs are applied to the models of the control levers and pedals.

Example # 2:

A method for the spatial design of civil aviation simulators has been developed. The method is as follows:

1) Initial stage:

· · · · · · ·

For civil aviation aircraft, the sequence of the method shall be used, the first two actions being performed for civil aviation aircraft with the relevant necessary input data. Other additional data are also applicable.

1.3) a comparison of the results of 1.1) and 1.2).

After performing the calculations and constructing the balancing diagrams from the samples and from the calculations obtained for the control levers and pedals, the following comparison is made and conclusions are drawn for further actions:

1.3.1) whether the deflection angles of the controls are increased and whether the spring (s) acting on the tensile used in the specimen will stretch more. The values obtained should be larger (in tension). If the condition is met, continue with the next action (below). If not returned in item 1.1), correcting the mistakes made and recalculating;

1.3.2) whether the deflection angles of the controls decrease and therefore whether the tensile springs used in the specimens will stretch less. The values obtained should be smaller (in tension). If the condition is fulfilled, proceed with the action in item 1.4) (below). If not returned in item 1.2), correcting the errors and recalculating.

1.4) after the calculation process is completed, a real or virtual layout is prepared. The model for civil aviation aircraft is for double occupancy cabs. The seat area of the seat is doubled and the distance between them is secured to the engine control handle stand. The layout only gets modified in terms of width. All other dimensions are retained in order to meet the Joint Aviation Requirements (JAR) requirements. The simulator layout is made in a decreasing scale. In order to reach the permissible limits for simulators for civil aviation aircraft, a magnifying scale is used, and the resulting simulator is obtained at a scale of M1: 1 according to the cab.

t • * n · • · · ····

The calculations preserve the deviations and efforts of the controls, shaping only the dimensions of the simulator (control levers, pedals, countertop, seats, axle, weight, test unit, engine control arm and springs) in on a larger scale. The standard dimensions (some of the dimensions of the pedals, control levers, seats, engine control knob, distances between some of them, etc.) measured by the cab are retained.

1.5) calculations of the springs used in

the samples of the control levers and pedals, taking the spring (diameter) R (D) of the permissible size limit to be constant [6].

When operating the control levers and pedals, small, small-pitch cylindrical coil springs are selected for tension.

From the results obtained for the controls (control levers and pedals), stiffness is selected and the dimensions of each spring are formed. The diameter adopted for structural reasons is initially taken on a magnifying scale as a constant for all springs applied to the control levers and pedals, and then selected at M1: 1 scale, again the diameter being a constant for all springs applied control levers and pedals.

1.6) combining the dimensions of three technological objects and creating a simulator:

1.6.1) the model of the simulator in descending scale;

1.6.2) of civil aviation aircraft;

1.6.3) of computer equipment (monitors).

In order to carry out the following steps from the steps and to obtain the dimensions of the simulator, the dimensions of the cockpit in the cockpit and the distance from the eyes of the pilot to the lantern or upper base of the aircraft shall be ensured.

2) Work stage including:

2.1) after the necessary dimensions have been provided, we proceed to:

2.1.1) splitting the boards into a certain number of monitors;

· · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · ·· ··· ·······

2.1.2) are calculated by the coefficient formulas - R _n ; the total coefficients - R _zy , R _xy , R _xz ; the coefficient for determining the monitors (for selecting the monitors) - R ₀ 6m ₀ ; coefficients for reducing the dimensions of the simulator in the planes zy, xy, xz - R _czy , R _C xy, R _cxz :

R _n = MM / TC

MM - the dimensions of the layout of the monitors

TC - dimensions of civil aviation aircraft dashboards

Rzy ^- Rnz + Rny

Rxy ^- Rnx + Rny for η - 1, 2, 3, 4

Rxz ~ Rnx + R _nz

Rnx, Rny, R _nz - coefficients equivalent to R _n , relative to

axes x, y, z η - number of monitors, by placement: 1 - main monitor (s) 2 - horizontal monitors 3 - vertical monitors 4 - monitor (s) positioned above the vertical and

main monitors

+ R _xz ) / c

Rzy, R _X y, R _xz - total coefficients in the planes O _zy , O _xy ,

Rzy, Rxy, Rxz - total coefficients in the planes O _zy , O _hu ,

The values obtained for R _n ;, R _zy , R _xy , R _xz ; R _O 6mo; Rczy, Rcxy, Rcxz are used to draw the simulator in 2D and 3D space, transfer the project to space, define boundary dimensions, define monitors and assemble it. The results of the formulas are plotted in a table for each plane O _zy , O _hu , O _xz .

2.1.3) monitors are selected. It is preferable to use 3D LCD touch screen display, extremely thin monitors.

• ·

• · · ·

Only 2D or 3D only can be taken. Due to the limited number of 3D monitors, they can be selected to be converted. This also allows the use of 3D glasses.

Dashboard results are plotted: t in a table, recording the dashboard type, monitor type, monitor number, width, height, diagonal, and base.

When choosing monitors, the distance from the eyes of the pilot to the lantern or the upper base of the aircraft shall be taken into account.

2.2) after the selection of the monitors, axonometric drawings are prepared in triplicate, with respect to the three coordinate planes O _xu , O _xz , O _yz . Apply to them the dimensions of the simulator on a magnifying scale and the boundary dimensions (the dimensions of item 2.1), separated by the coefficients R _czy , R _cxy , Rcxz in the planes of those on a magnifying scale.

2.3) From the dimensions obtained in a constructive way, the actual dimensions are selected. The actual dimensions are taken from the limit sizes by the allowable limits. They can be reduced below the limit, only if it is consistent with the structure and the cab. Spatial drawings are made in a type of isometry such as NE Isometric for components. The entire simulator is then assembled virtually on a software product.

2.4) the simulator thus obtained is determined to be acceptable according to its actual dimensions in 3D space and prepared for drawing in 2D space for working drawings.

3) Final stage, including:

3.1) spring computations are performed for 3D the plain at necessary output data: Pmin - minimum load, attached on the handles for steering and pedals; _Pax - maximum load, attached on the handles for

steering and pedals;

х _в , Хел., Хн - coordinates of deviation of the control bodies;

G - modulus of angular deformation of spring steel С70;

Tdop. - allowable tangential stress;

R (D) - reduced radius (diameter) of the flight simulator spring in Ml: l. R (D) is a constant for all springs, · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · ··· ······· applied to simulators for civil aviation aircraft in stage 3) at M1: 1 scale.

3.1.1) calculate the maximum torque M _cp ;

3.1.2) the maximum spring tension max f is calculated;

3.1.3) check the maximum tangential stress for the dimensioning of the pure torsion section:

3.1.3.1) the diameter of the cross section d is calculated;

3.1.3.2) calculate the number of active turns i;

3.1.3.3) record the result of the number of active turns i;

3.1.3.4) select springs.

3.1.4) calculate the minimum light aperture of 5 _m i _n ;

3.1.5) the initial light aperture δο is calculated;

3.1.6) the initial (free) length Lo is calculated;

3.1.7) calculate the length after loading max P L ₂ ;

3.1.8) calculate the length after loading min P Li;

3.1.9) calculate the lengths of the tensile springs fi and f ₂ ;

3.1.10) calculate the slope angle of the screw line a:

3.1.10.1) calculate the pitch of the springs h and record the dimensions d, D, δο, Lo and i of the springs.

3.1.11) calculate the length of screw line 1;

3.1.12) calculate the spring constant with;

3.1.13) select the number of turns i according to the distances obtained by the dimensions of the samples of the control levers and the pedals;

3.1.14) repetition of item 3.1.1), item 3.1.2), item 3.1.3) and item 3.1.3.1) is performed;

3.1.15) for the selected values of the number of active turns i, the maximum spring tension max f is calculated again.

When transferring springs from 3D to 2D space, changes occur that affect the images in the working drawings.

For this purpose, the Oxyz coordinate system is used, for each plane a coefficient k _zy , k _xy , k _{xz is determined} . The coefficients k _zy , k _xy , k _xz are • «· ♦ ο • · • · • · · · · equivalent to (k). For each maximum stretch of the springs max f, relative to the length after loading min P Li and the number of turns i, the required space coefficient for all planes Ozy, Oxy, Oxz, taking into account the coefficients R _czy , Rcxy, R _cxz of 2.1, is taken. and is recorded using the Oxyz coordinate system.

The springs are then calculated by taking the allowable value of the coefficient for the springs in space (k) multiplied by the coefficient with the maximum stretching of the spring. Ie (k) * max f.

3.1.16) is found from the maximum spring tension max f value of the coefficient for the springs in space:

3.1.16.1) previous maximum stretches max f se

divide the coefficients to reduce the dimensions of the simulator in the plane zy, xy, xz, ie R _czy , R _cxy , R _cxz ;

3.1.16.2) from item 3.1.15) take the newly obtained maximum springs of max f;

3.1.16.3) the newly obtained maximum stretches max f are multiplied by the coefficients for reducing the dimensions of the simulator in the plane zy, xy, xz, i.e. on R _czy , R _cxy , R _cxz ;

3.1.16.4) obtain coefficients for the springs in space (k) for each plane Ozy, Oxy, Oxz.

The arrangement of the springs determines in which plane the action is carried out and which coefficient will be used. The following additional calculations are made that determine (prove) the operation of the controls (controls and pedals), ie. and the operation of the springs.

3.1.17) springs are selected;

3.1.18) the values of the minimum bright aperture 6 _t , _n are taken from item 3.1.4);

3.1.19) additional calculations are made of the initial bright aperture δο;

3.1.20) additional calculations are made at the initial (free) length Lo;

3.1.21) make additional calculations of the length after loading max P L ₂ according to the formula:

L ₂ = Lo + max f + (k) * max f • · · · · · · · · · · · · · · · · · ·

3.1.22) make additional calculations of the length after loading min P C;

3.1.23) additional calculations of the spring lengths at stretching f] and f _{2 are made} ;

3.1.23.1) safi; 3.1.23.2) for f ₂ .

3.1.24) make additional calculations of the angle of inclination of the screw line a:

3.1.24.1) additional calculations of the spring step h are made.

The dimensions of the springs are described as: d, D, δο, Lo, i.

3.1.25) additional calculations are made for the length of the screw line 1;

3.1.26) additional calculations of the spring constant with the formula:

c = max P / (max f + (k) * max f)

3.2) In accordance with the calculations obtained, the springs are applied to the models of the control levers and pedals.

Example # 3:

A method for the spatial design of helicopter simulators has been developed. The method is as follows:

1) Initial stage:

For helicopters, the sequence of the method is used, the first two steps being performed for the helicopters with the corresponding necessary input data. Other additional data are also applicable.

1.3) a comparison of the results of 1.1) and 1.2).

After performing the calculations and constructing the balancing diagrams of the samples and the calculations obtained for the control lever (s) and pedals, the following comparison is made and conclusions are drawn for further actions:

1.3.1) whether the deflection angles of the controls are increased and whether the spring (s) acting on the tensile used in the specimen will stretch more. The values obtained should be larger (in tension). If the set condition is fulfilled, the next action (below) is continued with • · · · · · · · · · · · · · · · · If not returned in item 1.1), correcting the mistakes made and recalculating;

1.3.2) whether the deflection angles of the controls decrease and therefore whether the tensile springs used in the specimens will stretch less. The values obtained should be smaller (in tension). If the condition is fulfilled, proceed with the action in item 1.4) (below). If not returned in item 1.2), correcting the errors and recalculating.

1.4) after the calculation process is completed, a real or virtual layout is prepared. The layout for single-deck helicopters is similar to that of Figures 1 and 2. In the double occupancy of the cab, the distance between the seating area doubles. Depending on the type of helicopter (single and double cab layout), the layout can only change in width. All other dimensions are retained in order to meet the Joint Aviation Requirements (JAR) requirements. The simulator layout is made in a decreasing scale. In order to reach the permissible limits for helicopter simulators, a magnifying scale is used, and the resulting simulator is obtained at the M1: 1 scale according to the cab.

The calculations preserve the deviations and the efforts of the controls, shaping only the dimensions of the simulator (control lever (s), pedals, top, seat (s), axle, weight, test-rig, control lever stand). of the engine and springs) on a larger scale. The standard dimensions (some of the dimensions of the pedals, of the control lever (s), seat (s), engine control lever, distances at some of them, etc.) measured by the cab are retained.

1.5) calculations of the springs used in the samples of the control lever (s) and pedals are taken, assuming the springs of radius (diameter) R (D) to be of a constant size limit [6].

When operating the control lever (s) and the pedals, small, small-pitch cylindrical coil springs are selected which will work in tension.

«· · · · · · · · · · ·

From the results obtained for the controls (control lever (s) and pedals), stiffness is selected and the dimensions of each dimension taken are taken on a magnifying scale, as a constant value for the control lever (s) and pedals applied. , and one spring.

initially, all springs are selected in the M1: 1 scale, the diameter being again the magnitude of all the springs applied to the lever (s) for then constant control and pedals.

1.6) combining the dimensions of three technological objects and creating a simulator:

1.6.1) the model of the simulator in descending scale;

1.6.2) per helicopter;

1.6.3) of computer equipment (monitors).

next actions from

In order to perform the simulator dimensions, the distance from the eyes is to provide the dimensions of the pilot to the lantern stages and to give the cockpit or the top a cabin and a helicopter base.

2) Work stage including:

2.1) after the necessary dimensions have been provided, we proceed to:

2.1.1) splitting the boards into a certain number of monitors;

2.1.2) are calculated by the coefficient formulas - R _n ; the total coefficients - R _zy , R _xy , R _xz ; monitor designation factor (for monitor selection) - Z _{0 total} ; coefficients for reducing the size of the simulator in the planes zy, xy, xz - R _czy , R _cxy , Rcxz:

R _n = MM / TC

MM - the dimensions of the layout of the monitors

TC - dimensions of helicopter boards at η = 1, 2, 3, 4

R _zy ^- Rnz R _ny

Rxy ⁼ Rnx + Rny

Rxz ^- Rnx + Rnz

Rnx, Rny, Rnz - coefficients equivalent to R _n , relative to the x, y, z η axes - the number of monitors, relative to the location:

· · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · ··

- main monitor (s)

- horizontal monitors

- vertical monitors

- monitor (s) positioned above the vertical and main monitors (s)

Ro6mo (Rzy + R;

Rzy, xy + Rxz) / 3

Rxy, Rxz - cumulative coefficients in the valleys O _zy, O _xy, θχζ

Rczy

Rzy,

Rzy / 2; R _cxy R _xy / 2; R _cxz Rxz / 2

Rxy, Rxz - cumulative coefficients in the valleys O _zy, O _xy, o _xz.

The values obtained for R _n ;, R _Z y, Rxy, R _xz ; Ro6 _mo ; Rczy, Rcxy, Rcxz are used to draw the simulator in 2D and 3D space, transfer the project to space, define boundary dimensions, define monitors and assemble it. The results of the formulas are plotted in a table for each plane O _zy , O _hu , O _xz .

2.1.3) monitors are selected. It is preferable to use 3D LCD touch screen display, extremely thin monitors. Only 2D or 3D only can be taken. Due to the limited number of 3D monitors, they can be selected to be converted. This also allows the use of 3D glasses or the manufacture of a pilot's helmet glass such as that of 3D glasses.

Dashboard results are recorded in a table, recording the type of dashboard, monitor type, monitor number, width, height, diagonal and base.

When selecting monitors, the distance from the eyes of the pilot to the lantern or the top of the helicopter is taken into account.

2.2) after the selection of the monitors, axonometric drawings are prepared in triplicate, with respect to the three coordinate planes O _xu , O _xz , O _yz .

Apply to them the dimensions of the simulator on a magnifying scale and the boundary dimensions (the dimensions of item 2.1), separated by the coefficients R _czy ,

Rcxy, Rcxz in the plains of those on a magnifying scale.

ft · ft ft ft ft ft ft ft ft ft «ft ft ft ft

2.3) From the dimensions obtained in a constructive way, the actual dimensions are selected. The actual dimensions are taken from the limit sizes by the allowable limits. They can be reduced below the limit, only if it is consistent with the structure and the cab. Spatial drawings are made in a type of isometry such as NE Isometric for components. The entire simulator is then assembled virtually on a software product.

2.4) the simulator thus obtained is determined to be acceptable according to its actual dimensions in 3D space and prepared for drawing in 2D space for working drawings.

3) Final stage, including:

3.1) 3D plane springs are calculated with the necessary input data:

P _m in - minimum load applied to the control lever (s) and pedals;

Pmx - maximum load applied to the control lever (s) and pedals;

х _в , Хел., х _н - coordinates of deviation of the control bodies;

G - modulus of angular deformation of spring steel С70;

Gdop. - allowable tangential stress;

R (D) - reduced radius (diameter) of the helicopter simulator spring in Ml: l. R (D) is a constant for all springs applied to the helicopter simulators in step 3) at M1: 1 scale.

3.1.1) calculate the maximum torque M _cp ;

3.1.2) the maximum spring tension max f is calculated;

3.1.3) check the maximum tangential stress of the ottoman _x when dimensioning the cross section of the pure twist ottoman _x <^ extra. '·

3.1.3.1) the diameter of the cross section d is calculated;

3.1.3.2) calculate the number of active turns i;

3.1.3.3) record the result of the number of active turns i;

3.1.3.4) select springs.

3.1.4) calculate the minimum clear aperture of 6 _m i _n ;

3.1.5) the initial light aperture δο is calculated;

3.1.6) the initial (free) length Lo is calculated;

3.1.7) calculate the length after loading max P L ₂ ;

3.1.8) calculate the length after loading min P L /

3.1.9) the lengths of the tensile springs fj and f ₂ are calculated;

3.1.10) calculate the slope angle of the screw line a:

3.1.10.1) calculate the pitch of the springs h and record the dimensions d, D, δο, Lo and i of the springs.

3.1.11) calculate the length of screw line 1;

3.1.12) calculate the spring constant with;

3.1.13) the number of turns i is selected according to the distances obtained by the dimensions of the samples of the control lever (s) and the pedals;

3.1.14) repetition of item 3.1.1), item 3.1.2), item 3.1.3) and item 3.1.3.1) is performed;

3.1.15) for the selected values of the number of active turns i, the maximum spring tension max f is calculated again.

When transferring springs from 3D to 2D space, changes occur that affect the images in the working drawings.

For this purpose, the Oxyz coordinate system is used, for each plane a coefficient k _zy , k _xy , k _{xz is determined} . The coefficients k _zy , k _xy , k _xz are equivalent to c (k). For each maximum stretch of the springs max f, relative to the length after loading min P Li and the number of turns i, the required space coefficient for all planes Ozy, Ohu, Oxz, taking into account the coefficients R _CZ y, Rcxy, Rcxz of 2.1. and is recorded using the Oxyz coordinate system.

The springs are then calculated by taking the allowable value of the coefficient for the springs in space (k) multiplied by the coefficient with the maximum stretching of the spring. Ie (k) * max f.

3.1.16) is found from the maximum spring tension max f value of the coefficient for the springs in space:

3.1.16.1) the previous maximal stretches max f are divided by the coefficients for the reduction of the dimensions of the simulator in the plane Zy, Hu, ΧΖ, i.e. Ha R _CZ y, Rcxy, Rcxzi • · · · • · · · ·

3.1.16.2) from item 3.1.15) take the newly obtained maximum springs of max f;

3.1.16.3) the newly obtained maximum stretches max f are multiplied by the coefficients for reducing the dimensions of the simulator in the plane zy, xy, xz, i.e. on R _czy , R _cxy , R _cxz ;

3.1.16.4) obtain coefficients for the springs in space (k) for each plane Ozy, Oxy, Oxz.

The arrangement of the springs determines in which plane the action is carried out and which coefficient will be used. The following additional calculations are made which determine (prove) the operation of the controls (control lever (s) and pedals), i. and the operation of the springs.

3.1.17) springs are selected;

3.1.18) the values of the minimum bright aperture of 5 _m j _n are taken

from item 3.1.4);

3.1.19) additional calculations are made of the initial bright aperture δο;

3.1.20) additional calculations are made at the initial (free) length Lo;

3.1.21) make additional calculations of the length after loading max P L ₂ according to the formula:

L ₂ - Lo + max f + (k) * max f

3.1.22) make additional calculations of the length after loading min P Lj;

3.1.23) additional calculations of the lengths of the tensile springs fi and f _{2 are made} :

3.1.23.1) PA;

3.1.23.2) for f ₂ .

3.1.24) make additional calculations of the angle of inclination of the screw line a:

3.1.24.1) additional calculations of the spring step h are made.

The dimensions of the springs are described as: d, D, δο, Lo, i.

3.1.25) additional calculations are made for the length of the screw line 1;

I · · · · · · · · · · · · · · · · · · · · · ·

3.1.26) additional calculations of the spring constant with the formula:

c = max P / (max f h- (k) * max f)

3.2) According to the calculations obtained, the springs are applied to the control lever (s) and pedals.

Example # 4:

A method for the spatial design of light aviation simulators has been developed. The method is as follows:

1) Initial stage:

For light aviation aircraft, the sequence of the method is used, the first two steps being performed for light aviation aircraft with the relevant necessary input data. Other additional data are also applicable.

1.3) a comparison of the results of 1.1) and 1.2).

After performing the calculations and constructing the balancing diagrams of the samples and the calculations obtained for the control lever (s) and pedals, the following comparison is made and conclusions are drawn for further actions:

1.3.1) whether the deflection angles of the controls are increased and whether the spring (s) acting on the tensile used in the specimen will stretch more. The values obtained should be larger (in tension). If the condition is met, continue with the next action (below). If not returned in item 1.1), correcting the mistakes made and recalculating;

1.3.2) whether the deflection angles of the controls decrease and therefore whether the tensile springs used in the specimens will stretch less. The values obtained should be smaller (in tension). If the condition is fulfilled, proceed with the action in item 1.4) (below). If not returned in item 1.2), correcting the errors and recalculating.

1.4) after the calculation process is completed, a real or virtual layout is prepared. The layout of single-cabin light aircraft aircraft is similar to that of Figures 1 and 2. For double occupancy in the cab, the distance of the placement area

the seat doubles. Depending on the type of aircraft (single and double cab layout), the layout can only change in width. All other dimensions are retained in order to meet the Joint Aviation Requirements (JAR) requirements. The simulator layout is made in a decreasing scale. In order to reach the permissible limits for a light aircraft simulator, a magnifying scale is used, and the resulting simulator is obtained at the M1: 1 scale according to the cab.

The calculations preserve the deviations and the efforts of the controls, shaping only the dimensions of the simulator (control lever (s), pedals, top, seat (s), axle, weight, test-rig, control lever stand). of the engine and springs) on a larger scale. The standard dimensions (some of the dimensions of the pedals, of the control lever (s), seat (s), engine control lever, distances at some of them, etc.) measured by the cab are retained.

1.5) calculations of the springs used in the samples of the control lever (s) and pedals are taken, assuming the springs of radius (diameter) R (D) to be of a constant size limit [6].

When operating the control lever (s) and the pedals, small, small-pitch cylindrical coil springs are selected which will work in tension.

From the results obtained for the controls (lever (s) and pedals), stiffness is selected and the dimensions of each spring are formed. The diameter adopted for structural reasons is initially incrementally scaled as a constant for all springs applied to the control lever (s) and pedals, and then selected at M1: 1 scale, again diameter constant for all springs applied to control levers and pedals.

1.6) combining the dimensions of three technological objects and creating a simulator:

1.6.1) the model of the simulator in descending scale;

1.6.2) light aircraft aircraft;

· · · · · · · · · ·

1.6.3) of computer equipment (monitors).

• · · · · · · · · · ·

In order to perform the following steps from the stages and to obtain the dimensions of the simulator, the dimensions of the cockpit in the cab and the distance from the eyes of the pilot to the lantern are provided.

2) Work stage including:

2.1) after the necessary dimensions have been provided, we proceed to:

2.1.1) splitting the boards into a certain number of monitors;

2.1.2) are calculated by the coefficient formulas - R _n ; the total coefficients - R _zy , R _xy , R _xz ; the coefficient for determining the monitors (for selecting the monitors) - R _O 6mo; coefficients for reducing the size of the simulator in the planes zy, xy, xz - R _czy , Rcxy, R _cxz :

R _n = MM / TC

MM - the dimensions of the layout of the monitors

TC - the dimensions of the aircraft aviation dashboard

Rxy Rnx + Rny

Rxz ^- Rnx Rnz for η = 1, 2, 3, 4

Rnx, Rny, Rnz - coefficients equivalent to R _n with respect to the x, y, z axes

η - number of monitors, by placement:

- main monitor (s)

- horizontal monitors

- vertical monitors

- monitor (s) positioned above the vertical and main monitors (s)

R _Z y, Rxy, Rxz - total coefficients in the planes O _zy , O _xy ,

CXZ Rxz! 2

···· ·

R _zy , Rxy, Rxz - total coefficients in the planes O _zy , O _xy , O _xz .

The values obtained for R _n ;, R _zy , R _xy , R _xz ; R _O 6mo; R _czy , R _cxy , Rcxz, used to draw the simulator in 2D and 3D space, transfer the project into space, define boundary sizes, define monitors and assemble it. The results of the formulas are plotted in a table for each plane O _zy , O _hu , O _xz .

2.1.3) monitors are selected. It is preferable to use 3D LCD touch screen display, extremely thin monitors. Only 2D or 3D only can be taken. Due to the limited number of 3D monitors, they can be selected to be converted. This also allows the use of 3D glasses.

Dashboard results are recorded in a table, recording the type of dashboard, monitor type, monitor number, width, height, diagonal and base.

When selecting monitors, the distance from the eyes of the pilot to the lantern is taken into account.

2.2) after the selection of the monitors, axonometric drawings are prepared in triplicate, with respect to the three coordinate planes O _xu , O _xz , O _yz . Apply to them the dimensions of the simulator on a magnifying scale and the boundary dimensions (the dimensions of item 2.1), divided by the coefficients R _CZ y, R _cxy , Rcxz in the planes of those on a magnifying scale.

2.3) From the dimensions obtained in a constructive way, the actual dimensions are selected. The actual dimensions are taken from the limit sizes by the allowable limits. They can be reduced below the limit, only if it is consistent with the structure and the cab. Spatial drawings are made in a type of isometry such as NE Isometric for components. The entire simulator is then assembled virtually on a software product.

2.4) the simulator thus obtained is determined to be acceptable according to its actual dimensions in 3D space and prepared for drawing in 2D space for working drawings.

3) Final stage, including:

3.1) 3D plane springs are calculated with the necessary input data:

Pmin - minimum load applied to the control lever (s) and pedals;

Pmx - maximum load applied to the control lever (s) and pedals;

х _в , х _ел ., Хн - coordinates of deviation of the controls;

G - modulus of angular deformation of spring steel С70;

t _extra . - allowable tangential stress;

R (D) - reduced radius (diameter) of a light aircraft flight simulator spring in Ml: l. R (D) is a constant for all springs applied to flight simulator simulators in step 3) on a scale of M1: 1.

3.1.1) calculate the maximum torque M _cp ;

3.1.2) the maximum spring tension max f is calculated;

3.1.3) check the maximum tangential stress of an ottoman _x when dimensioning the cross section of a pure torsion of an ottoman _x <Tdop. ·

3.1.3.1) the diameter of the cross section d is calculated;

3.1.3.2) calculate the number of active turns i;

3.1.3.3) record the result of the number of active turns i;

3.1.3.4) select springs.

3.1.4) calculate the minimum clear aperture of 8 _m i _n ;

3.1.5) the initial light aperture δο is calculated;

3.1.6) the initial (free) length Lo is calculated;

3.1.7) calculate the length after loading max P L ₂ ;

3.1.8) calculate the length after loading min P Li;

3.1.9) the lengths of the springs P and f ₂ are calculated;

3.1.10) calculate the slope angle of the screw line a:

3.1.10.1) calculate the pitch of the springs h and record the dimensions d, D, δο, Lo and i of the springs.

3.1.11) calculate the length of screw line 1;

3.1.12) calculate the spring constant with;

· <·· 4 • · • · · · · 4 · 4 4 • · · · · 4 · · · · · · · · · · · · · • t · · 4 4 4 ·· ·· ·· ·· · · · · · · · ·

3.1.13) the number of turns i is selected according to the distances obtained by the dimensions of the samples of the control lever (s) and the pedals;

3.1.14) repetition of item 3.1.1), item 3.1.2), item 3.1.3) and item 3.1.3.1) is performed;

3.1.15) for the selected values of the number of active turns i, the maximum spring tension max f is calculated again.

When transferring springs from 3D to 2D space, changes occur that affect the images in the working drawings.

For this purpose, the Oxyz coordinate system is used, for each plane a coefficient k _zy , k _xy , k _{xz is determined} . The coefficients k _zy , k _xy , k _xz are equivalent to c (k). For each maximal stretch of the springs max f, relative to the length after loading min P L] and the number of turns i, the required space coefficient for all planes Ozy, Oxy, Oxz, taking into account the coefficients R _czy , R _C xy> Rcxz of m. 2.1) and is recorded using the Oxyz coordinate system.

The springs are then calculated by taking the allowable value of the coefficient for the springs in space (k) multiplied by the coefficient with the maximum stretching of the spring. Ie (k) * max f.

3.1.16) is found from the maximum spring tension max f value of the coefficient for the springs in space:

3.1.16.1) the previous maximum stretches max f are divided by the coefficients for reducing the dimensions of the simulator in the plane zy, xy, xz, that is, R _czy , R _cxy , R _cxz ;

3.1.16.2) from item 3.1.15) take the newly obtained maximum springs of max f;

3.1.16.3) the newly obtained maximum stretches max f are multiplied by the coefficients for reducing the dimensions of the simulator in the plane zy, xy, xz, i.e. on R _CZ y, R _CX y, Rcx _Z ;

3.1.16.4) obtain coefficients for the springs in space (k) for each plane Ozy, Oxy, Oxz.

The arrangement of the springs determines in which plane the action is carried out and which coefficient will be used. The following additional calculations are made that determine (prove) the work of the authorities

for control (lever (s) and pedals), i. and the operation of the springs.

3.1.17) springs are selected;

3.1.18) the values of the minimum bright aperture of 8 _min shall be taken from item 3.1.4);

3.1.19) carry out se additional calculations on the initial one bright hole δο; 3.1.20) carry out se additional calculations on the initial (free) length Lo; 3.1.21) perform se additional calculations on the length

after loading max P L ₂ according to the formula:

L ₂ - Lo + max f + (k) * max f

3.1.22) make additional calculations of the length after loading min P Li;

3.1.23) additional calculations of the lengths of the tensile springs fi and f _{2 are made} :

3.1.23.1) for fi; 3.1.23.2) for f ₂ .

3.1.24) make additional calculations of the angle of inclination of the screw line a:

3.1.24.1) additional calculations of the spring step h are made.

The dimensions of the springs are described as: d, D, δο, Lo, i.

3.1.25) additional calculations are made for the length of the screw line 1;

3.1.26) additional calculations of the spring constant with the formula:

c = max P / (max f + (k) * max f)

3.2) in accordance with the calculations obtained, the springs are applied to the control lever (s) and pedals.

Example # 5:

A method for the spatial design of military aviation simulators has been developed. The method is as follows:

1) Initial stage:

• 9

For military aviation aircraft, the sequence of the method is used, the first two steps being performed for military aviation aircraft with the relevant necessary input data. Other additional data are also applicable.

1.3) a comparison of the results of 1.1) and 1.2).

After performing the calculations and constructing the balancing diagrams of the samples and the calculations obtained for the control lever (s) and pedals, the following comparison is made and conclusions are drawn for further actions:

1.3.1) whether the deflection angles of the controls are increased and whether the spring (s) acting on the tensile used in the specimen will stretch more. The values obtained should be larger (in tension). If the condition is met, continue with the next action (below). If not returned in item 1.1), correcting the mistakes made and recalculating;

1.3.2) whether the deflection angles of the controls decrease and therefore whether the tensile springs used in the specimens will stretch less. The values obtained should be smaller (in tension). If the condition is fulfilled, proceed with the action in item 1.4) (below). If not returned in item 1.2), corrected

mistakes made and recalculated.

1.4) after the calculation process is completed, a real or virtual layout is prepared. The layout for single-cabin military aircraft is similar to that of Figures 1 and 2. In the double occupancy of the cab, the distance between the seating area doubles. Depending on the type of aircraft (single and double cab layout), the layout can only change in width. All other dimensions are retained in order to meet the Joint Aviation Requirements (JAR) requirements. The simulator layout is made in a decreasing scale. In order to reach the permissible limits for flight simulators for military aviation, a magnifying scale is used, and the resulting simulator is obtained at a scale of M1: 1 according to the cabin.

• · · · ·

The calculations preserve the deviations and the efforts of the controls, shaping only the dimensions of the simulator (control lever (s), pedals, top, seat (s), axle, weight, test-rig, control lever stand). of the engine (s) and springs) on a larger scale. The standard dimensions (some of the dimensions of the pedals, the control lever (s), seat (s), engine control lever (s), distances at some of them, etc.) measured by the cab are retained).

1.5) calculations of the springs used in the samples of the control lever (s) and pedals are taken, assuming the springs of radius (diameter) R (D) to be of a constant size limit [6].

When operating the control lever (s) and the pedals, small, small-pitch cylindrical coil springs are selected which will work in tension.

From the results obtained for the controls (lever (s) and pedals), stiffness is selected and the dimensions of each spring are formed. The diameter adopted for structural reasons is initially taken on a magnifying scale as a constant for all springs applied to the control lever (s) and pedals, and then selected at M1: 1 scale, again being a constant for all springs applied to the control lever (s) and pedals.

1.6) combining the dimensions of three technological objects and creating a simulator:

1.6.1) the model of the simulator in descending scale;

1.6.2) of aircraft from military aviation;

1.6.3) of computer equipment (monitors).

In order to perform the following steps from the stages and to obtain the dimensions of the simulator, the dimensions of the cockpit in the cab and the distance from the eyes of the pilot to the lantern are provided.

2) Work stage including:

2.1) after the necessary dimensions have been provided, we proceed to:

2.1.1) splitting the boards into a certain number of monitors;

• · · ·

2.1.2) are calculated by the coefficient formulas - R _n ; the total coefficients - R _zy , R _xy , R _xz ; the coefficient for determining the monitors (for selecting the monitors) - R _O 6mo; coefficients for reducing the size of the simulator in the planes zy, xy, xz - R _czy , R _cxy , R _cxz :

R _n = MM / TC

MM - the dimensions of the layout of the monitors

TC - the dimensions of the dashboard of a military aircraft

Rzy ^: Rnz + Rny

Rxy ~ Rnx + Rny for n = 1, 2, 3, 4

Rxz ^- Rnx + Rnz

Rnx, Rny, R _nz - coefficients equivalent to R _n , relative to the x, y, z η axes - number of monitors, relative to the location:

- main monitor (s)

- horizontal monitors

- vertical monitors

- monitor (s) positioned above the vertical and main monitors (s)

K-total (Rzy Rxy + Rxz) f 3

Rzy, Rxy, R _xz - cumulative coefficients in the valleys O _zy, O _xy, © 0 "

Rczy ~ Rzy! 2; Rcxy ^- Rxy I 2; R _cxz - R _xz / 2

Rzy, Rxy, Rxz - total coefficients in the planes O _zy , O _hu , θχζ ·

The values obtained for Rnj, Rzy, Rxy, Rxz, R <> 6inoj Rczy, Rcxy, Rcxz will be used to draw the simulator in 2D and 3D space, transfer the project to the space, define boundary dimensions, define monitors and assemble it . The results of the formulas are plotted in a table for each plane O _zy , O _hu , O _xz .

2.1.3) monitors are selected. It is preferable to use 3D LCD touch screen display, extremely thin monitors.

• ft · · • ft

Only 2D or 3D only can be taken. Due to the limited number of 3D monitors, they can be selected to be converted. This also allows the use of 3D glasses or the manufacture of a pilot's helmet glass such as that of 3D glasses.

Dashboard results are recorded in a table, recording the type of dashboard, monitor type, monitor number, width, height, diagonal and base.

When selecting monitors, the distance from the eyes of the pilot to the lantern is taken into account.

2.2) after the selection of the monitors, axonometric drawings are prepared in triplicate, with respect to the three coordinate planes O _xu , O _xz , O _yz . Apply to them the dimensions of the simulator on a magnifying scale and the boundary dimensions (the dimensions of item 2.1), divided by the coefficients R _czy , Rcxy, Rcxz in the planes of those on a magnifying scale.

2.3) From the dimensions obtained in a constructive way, the actual dimensions are selected. The actual dimensions are taken from the limit sizes by the allowable limits. They can be reduced below the limit, only if it is consistent with the structure and the cab. Spatial drawings are made in a type of isometry such as NE Isometric for components. The entire simulator is then assembled virtually on a software product.

2.4) the simulator thus obtained is considered acceptable

according to its actual dimensions in 3D space and preparing to draw in 2D space for working drawings.

3) Final stage, including:

3.1) 3D plane springs are calculated with the necessary input data:

Pmin - minimum load applied to the control lever (s) and pedals;

I yell - the maximum load applied to the control lever (s) and pedals;

х _в , Хел., Хн - coordinates of deviation of the control bodies; G - modulus of angular deformation of spring steel С70;

Tdop. - allowable tangential stress;

R (D) - reduced radius (diameter) of the flight simulator spring in Ml: l. R (D) is a constant for all springs applied to flight simulators in the military aviation stage

3) on a scale of M1: 1.

3.1.1) calculate the maximum torque M _cp ;

3.1.2) the maximum spring tension max f is calculated;

3.1.3) check the maximum tangential stress of an ottoman _x when dimensioning the cross section of a pure twist of an ottoman _x <

Gdop:

3.1.3.1) the diameter of the cross section d is calculated;

3.1.3.2) calculate the number of active turns i;

3.1.3.3) record the result of the number of existing

coils i;

3.1.3.4) select springs.

3.1.4) the minimum clear opening of 8 _t is calculated; _n ;

3.1.5) the initial light aperture δο is calculated;

3.1.6) the initial (free) length Lo is calculated;

3.1.7) calculate the length after loading max P L ₂ ;

3.1.8) calculate the length after loading min P Lj;

3.1.9) calculate the lengths of the tensile springs fi and f ₂ ;

3.1.10) calculate the slope angle of the screw line a:

3.1.10.1) calculate the pitch of the springs h and record the dimensions d, D, δο, Lo and i of the springs.

3.1.11) calculate the length of screw line 1;

3.1.12) calculate the spring constant with;

3.1.13) the number of turns i is selected according to the distances obtained by the dimensions of the samples of the control lever (s) and the pedals;

3.1.14) repetition of item 3.1.1), item 3.1.2), item 3.1.3) and item 3.1.3.1) is performed;

3.1.15) for the selected values of the number of active turns i, the maximum spring tension max f is calculated again.

• ·· ·

When transferring springs from 3D to 2D space

changes occur that affect the images in the working drawings.

For this purpose, the Oxyz coordinate system is used, for each plane a coefficient k _zy , k _xy , k _{xz is determined} . The coefficients k _zy , k _xy , k _xz are equivalent to c (k). For each maximum stretch of the springs max f, relative to the length after loading min P Li and the number of turns i, the required space coefficient for all planes Ozy, Oxy, Oxz, taking into account the coefficients R _CZ y, Rcxy, R _C x _Z from m 2.1) and is recorded using the Oxyz coordinate system.

The springs are then calculated by taking the allowable value of the coefficient for the springs in space (k) multiplied by the coefficient with the maximum stretching of the spring. Ie (k) * max f.

3.1.16) is found from the maximum spring tension max f value of the coefficient for the springs in space:

3.1.16.1) the previous maximum stretches max f are divided by the coefficients for reducing the dimensions of the simulator in the plane zy, xy, xz, that is, R _czy , R _CX y, R _cxz ;

3.1.16.2) from item 3.1.15) take the newly obtained maximum springs of max f;

3.1.16.3) the newly obtained maximum stretches max f are multiplied by the coefficients for reducing the dimensions of the simulator in the plane zy, xy, xz, i.e. on R _czy , Rcxy, Rcx _Z ;

3.1.16.4) obtain coefficients for the springs in space (k) for each plane Ozy, Oxy, Oxz.

The arrangement of the springs determines in which plane the action is carried out and which coefficient will be used. The following additional calculations are made which determine (prove) the operation of the controls (control lever (s) and pedals), i. and the operation of the springs.

3.1.17) springs are selected;

3.1.18) the values of the minimum bright aperture of 5 _m j _n are taken from item 3.1.4);

3.1.19) additional calculations are made of the initial bright aperture δο;

-A

• «· · «· • · · • · · · · • · · & • Mr 4 » • · · · * · · · • · 9 · * · · L • • · · · • · · · · · · • · · · · 3.1.20) carry out are extra calculations on the initial (free) length Lo; 3.1.21) perform are extra calculations on the length after loading max P L ₂ on the formula: L ₂ = Lq + max f + (k) * max f 3.1.22) perform are extra calculations on the length

after loading min P C;

3.1.23) additional calculations of the lengths of the tensile springs fj and f _{2 are made} :

3.1.23.1) Zay; 3.1.23.2) for f ₂ .

3.1.24) make additional calculations of the angle of inclination of the screw line a:

3.1.24.1) additional calculations of the spring step h are made.

The dimensions of the springs are described as: d, D, δο, Lo, i.

3.1.25) additional calculations are made for the length of the screw line 1;

3.1.26) additional calculations of the spring constant with the formula:

c = max P / (max f + (k) * max f)

3.2) According to the calculations obtained, the springs are applied to the control lever (s) and pedals.

The embodiments of the simulator construction using the spatial design method for flight and spacecraft simulators are explained using the following exemplary embodiments:

Example # 6:

In the design of spacecraft (Fig. 10), a change occurs when the plate (1) is formed - it is designed wider due to the use of a double seat. Six monitors (21) are installed and as many as are calculated for the upper base of the room.

The location of the engine control handle stand (8) depends on the type of apparatus. The control lever (3) is also positioned according to its location. The pattern is the same. Is used

................ connecting two identical models of the control lever (H). The dimensions (D) of the springs remain constant. There is no change in the pedal pattern (2) as well as the dimensions (D) of the springs. Changes are made to their number (two identical samples are used that are not connected to each other such as the control lever (3), since the computational work is complicated) and the sizes according to the calculations. By connecting the specimens to the computer (s), the specimens of both the control levers (3) and the pedals (2) are enabled to make compatible motions, such as a single specimen of the control lever (3), when deviating in a given direction, the other control lever (H) is also diverted in the same direction. The size of the monitors (21) varies depending on the calculations. The test fixture (9) has no design change. The only change is the number of recorders. A change in seat structure (4) occurs using a connecting structure for two identical seats (4), between which, depending on the location of the engine control lever, the engine control handle stand (8) may be designed. The axis (5) passes through the top (1) again. The coupling of the control levers (3) and the coupling of the seats (4) is adhered to by a support (weight) (6). With the support (weight) (6), when the changes in dimensions occur, its weight changes. It is in accordance with the structure obtained when performing the calculations. The software part is for the spacecraft type, respectively.

When using a propulsion system (Fig. 12), the construction of Figs. 10 is constructed as a closed system and is fixed to the circular surface (25) and to the drive system itself. The propulsion system consists of two rotating rings (22) perpendicular to each other and secured to posts (23) for the floor of the room. A single automatic key (27) is used for braking. The seats (4) shall be fully projected downwards. They are fitted with seat belts (28) to support the astronauts. After moving the seats (4), a holder (26) is attached to the cab, which holds them to the circular surface (25). The circular surface (25) engages the rotating rings (22) of the drive system. A congestion-generating device (24) is mounted below the circular surface (25).

--- and ... ...

* 9-

Example # 7:

For civil aviation flight simulators, a structure similar to that for spacecraft with the only difference in size is applied (Fig. 10). It shall not be secured to a propulsion system to which an overloading device is attached. Only the dimensions (D) of the spring remain constant. The software part is for the aircraft type.

Example # 8:

For helicopter simulators, both single-deck helicopters shall be designed (using the design of the aviation simulator designed according to the method) (Fig. 3, Fig. 9) and double (similar to that of spacecraft) ( Fig. 10), with the only difference in size. Depending on the purpose of the helicopter, the structure can also be attached to a propulsion system to which an overloading device is attached (Fig. 11, Fig. 12). Only the dimensions (D) of the spring remain constant. The software part is for the helicopter type.

Example # 9:

In light aviation, single and side-by-side pilots in the cockpit of aircraft are used. For double occupancy in the cabin, the construction is similar to that of spacecraft with the only difference in size (Fig. 10). Only the dimensions (D) of the spring remain constant. The software part is for aircraft type.

For single-deck airplanes, the design of the aviation simulator designed according to the method is used, and a change occurs in dimensions (Fig. 3, Fig. 9). Only the dimensions (D) of the spring remain constant. The software part is for the aircraft type.

For triple-gliders, a change in design occurs in the number of monitors: three monitors are used, the control lever (a trapeze is drawn with a spring) and the width of the countertop. A change in size occurs. Only the dimensions (D) of the pedal springs and that of the trapezoid remain constant. The software part is for trike planes, respectively.

Depending on the purpose of the aircraft, the structure may also be attached to a propulsion system to which an overloading device is attached (Fig. 11, Fig. 12).

Example # 10:

In military aviation, single and seated pilot seats are used. When positioned side by side, the construction is similar to that of spacecraft with the only difference in size (Fig. 10). Only the dimensions (D) of the springs remain constant. The software part is appropriate for the aircraft type.

For single-seat aircraft, the design of the aviation simulator, designed according to the method, is used, as changes occur in size (Fig. 3, Fig. 9). Only the dimensions (D) of the springs remain constant. The software part is appropriate for the aircraft type.

Depending on the purpose of the aircraft, the structure may also be attached to a propulsion system to which an overload generating device is attached (Fig. 11, Fig. 12).

An aeronautical simulator designed in accordance with the spatial design method for flight and spacecraft simulators relates, in particular, to a single-cabin desktop simulator intended for pilot training. It is designed for Pilatus aircraft (PC-9M) and can be used for single cabin aircraft (Fig. 9).

The application of the spatial design method for flight and spacecraft simulators to the Pilatus aircraft referred to above as an example above shall be carried out in the following sequence: when performing action 1.1) from the initial stage, the required longitudinal baseline data shall be:

1.1.1) carry out the calculations necessary to construct the balance diagrams of the deflection of the rudder by height;

• · · ·

1.1.2) constructs the balance diagram of the deviation of the rudder by height versus speed: δ _Β = f (V);

1.1.3) perform the calculations necessary to construct the balance diagrams by the effort transmitted to the control lever when deflecting the rudder for height P _in ;

1.1.4) draws a balance diagram of the effort transmitted to the control lever when the rudder is deflected for height P _in velocity: P _in = f (V);

1.1.5) Shapes the balancing diagram of the effort transmitted to the steering control when deflecting the rudder by height P _in the distance measured from the cab by the displacement of the steering lever when deflecting the rudder by height x _in : P _in = f

C (Min):

1.1.5.1) draws a balancing chart on the rudder deviation for height altitude δ _Β for speed, for cruise speed of flight Y _crossover : δ _Β = f (V);

1.1.5.2) constructs a balancing diagram of the displacement of the control lever measured by the cab when the rudder is deviated by height x _in relation to the speed at x _in = δ _Β : x _in = f (V);

1.1.5.3) plot the balance diagrams of the effort transmitted to the control lever when the rudder is deflected by height P _in velocity V: P _in = f (V) and measured by the cab

A distance of movement of the control lever for biasing the elevator x _in relation to the speed V: x _in = f (V) for cruising flight speed V _Kreis.

From these, a balancing chart is made of the effort transmitted to the steering control when deflecting the rudder by height P _in relation to the distance measured from the cab by the displacement of the steering lever when deflecting the rudder by height x _in : P _in = f (x _in ). From P _c = f (x _c ) it is possible to determine how far x _{c the} control lever moves when the required force P _{c is applied} ;

1.1.6) calculate the effort transmitted to the control lever when deflecting the rudder when maneuvering against the speed and construct the balance diagrams (dP _B / dn _y ) = f (V).

···· *

For the calculation and construction is taken from maximum positive to maximum negative overload n _y.

When performing action 1.2) from the initial stage, the necessary lateral traffic data outputs are:

1.2.1) carry out the calculations necessary to construct the balance diagrams of the rudder deviation of the direction δ _Η : To construct the balance diagrams for lateral movement, the following shall be calculated:

A) At the crossroads:

1) the steering angle of the rudder;

2) pedal effort.

1.2.2) plot the balance diagram of the rudder deviation for the direction δ _{Η with} respect to the sliding angle β: δ _Η = f (β);

1.2.3) perform the calculations necessary to construct the balancing chart by the angle of roll γ;

1.2.4) plot a balance diagram of the rudder deviation for the direction δ _Η relative to the angle of roll γ: δ _Η = f (γ);

1.2.5) make calculations for the balancing chart on the effort transmitted to the P _n pedals;

1.2.6) plot the balancing diagram of the effort transmitted to the pedals P _{n with} respect to the sliding angle β: P _n = f (β);

1.2.7) plot the balancing diagram of the effort transmitted to the pedals P _{n with} respect to the angle of roll γ: P _n = f (γ).

To construct the lateral balance diagrams, the following is calculated:

B) At transverse moment:

1) the angle of deviation of the ailerons;

2) efforts transmitted to the control lever;

1.2.8) carry out the calculations necessary to construct the balancing diagrams of the ailerons;

1.2.9) constructs the balancing diagram along the angle of deflection of ailerons 5 _{el with} respect to the sliding angle β: b _el . ⁼ f (β);

1.2.10) constructs the balancing diagram on the angle of deviation of the ailerons 8 _el . relative to the roll angle γ: 5 _el . = f (γ);

• ^*: · ::: ·: ·:

· · · · · · · · · · · ·.

1.2.11) perform the calculations necessary to construct the balance diagrams by the effort transmitted to the control lever when deflecting the ailerons P _el . relative to the sliding angle β: P _e ". = f (P);

1.2.12) constructs a balancing diagram of the effort transmitted to the control lever when deflecting the ailerons P _el . relative to the roll angle γ: P _el = f (γ).

The sequence of the following steps of the steps was performed by the method of spatial design of simulators for aircraft and spacecraft. The final result of an exemplary Pilatus aircraft (PC-9M), which is also applicable to single-pilot aircraft in the cockpit, is described in the figures.

In FIG. 3 is an axonometric view of such a simulator. It consists of: five computers (7) with monitors (21) 3D LCD touch screen display, extremely thin. The monitors (21) have been selected extremely thin to shape the cabin, with a touch screen display to allow the buttons to be pressed by hand, and 3D visualization conveys more clarity in the cabin.

The monitors (21) are determined according to the method of spatial design of size simulators. The hob (1) they are mounted on is designed to meet the requirements of JAR (Joint Aviation Requirements). It provides a constant minimum directional visual field of view with 45 ° horizontal and 30 ° vertical field of view, as well as a permanent oblique to the cockpit minimum directional visual field view, providing 180 ° horizontal and 40 ° vertical field of view for each pilot. The hob (1) sticks to the floor of the room with supports (13). The supports (13) are fixed to it and the floor with nuts and bolts.

The pedals (2) are attached to the countertop (1). The airplane control lever (3) is stationary.

The seat (4) is movable and moves back to seat the pilot. It then moves forward along the axis (5) and is held in place by a nut. The support (6) balances the structure and prevents the seat and nut from being pulled back out.

In FIG. 4 shows the simulator in the main view. A weight is provided in front of the weight (6) which prevents the axle (5) from being screwed to the weight

(6) obtained by moving the seat (4) loosening. In order to ensure that the structure is balanced, apart from the support (weight) (6), the axis (5) is attached externally to the hob (1).

The computer exported from the front connects to the tester (9). The testing device (9) has a button that is pressed after the pilot data processing fields are completed. It is related to the location of the printer. Therefore, a setting for its connection to the printer for displaying the processed information is added to the software itself.

The support of the engine control lever (8) is fixed to the hob (1) and is stationary.

The pedals (2) are also attached to the raft (1). The lift (adjuster) (14), after being adjusted by the pedal adjustment lever (2) from the cab, is inserted into the profile (12) and secured to the hob (1) by a strap (10). The plate (10) is inserted into the article X (11). The upper part of the lift (regulator) (14) is movable 90 ° upwards and is held with the ear (15).

Figure 5 shows the aviation simulator from above. This allows one to see in detail the simulator inside. The computers (7) are on the outside and one on the front (right / left) of the pedals (2). The computer (7) connecting to the tester (9) is moved left / right sideways so that the pedals (2) can be pulled while adjusting. The tester (9) also displays a display showing the flight results.

The location of the engine control handle stand (8) is located relative to the horizontal left monitor (21). The airplane control lever (3) sticks sideways to the pedals (2) with a portion of the axle (5) larger in diameter and with a seat nut (4). It is fixed to the floor.

From the inside, ie. where no seat is drawn (4) and where the airplane control lever (3) is fitted, no supports are placed outside. Only there the supports (13) are mounted inside. This is intended to allow the seat (4) and the pilot to move within the interior of the structure.

In FIG. 6 shows the aircraft simulator, viewed from behind. It shows more clearly the profile for the engine control handle stand (8). It grips the hob (1) and passes through the horizontal left monitor (21). The joystick of the engine control lever is positioned on the raised end portion next to the vertical left monitor (21).

Due to the pull of the pedals (2) back, there is an opening depending on the height (s) of the pilot (s) who will operate the aircraft.

Up to the simulator described here, the seat (4) was closed with a nut. In FIG. 7 depicts a mechanism by which the seat can also be restrained. This mechanism consists of a flange (16) with an opening having a diameter equal to that of the axis (5). On the side are movable grips (17) which, after pulling the seat (4), rotate forward about both axes 90 °. g-° ^{b The slotted} profiles (18) on which the closing brackets (19) are located are also rotated 90 ° and locked. The opening between the two brackets has a diameter equal to the axis (5). They can be unlocked with the special key (20) shown in Fig. 8.

Application (use) of the invention

In the implementation of the Pilatus aircraft simulator (PC-9M) method, as well as in other apparatus in step 1 of action 1.1), when performing the calculations necessary to construct the balance diagrams of the deflection of the rudder, a situation which is solved in the following way: in determining the angle of rotation of the elevator δ _Β, if the value of the coefficient of lateral moment in zero lift m _z o is unknown and can not be taken, the decision is to accept m _z o = 0, but then To build proper Balancing diagrams corresponding to the actual take cruising flight speed Vicpefic. and build a real balancing chart.

In step 1 of action 1.1) when performing the calculations required for the construction of The trim diagrams in the efforts transmitted to the control lever for biasing the elevator P _in can be obtained values for the force P _in and hinge moment M _Swe of maximum to the minimum as the number of

Max M corresponds to the minimum value. This is due to the unknown value of the coefficient of lateral moment at zero lift force m _z o (since the angle of deviation of the rudder by height δ _Β from the number of Mach M increases, but with negative values, the force applied to the control lever for deflection of the rudder for height P _in decreases). In order to increase the cruise speed of flight V _Kpeft c in order to increase the force applied to the control lever when deflecting the rudder by height P _{in the} number of Mach M. and therefore the steering angle of elevation δ _Β will also increase, i.e. by increasing the steering angle by height δ _уси , the force exerted on the control lever when deflecting the steering height P _into at speed increases.

In Step 1 of Action 1.2), in order to limit the amount of calculation in calculating the angle of attack, where the aerodynamic derivative of the lift coefficient from the angle of attack C ' _y is taken according to the number of Mach M, the following is done: for example for subsonic aircraft M = 0.1 ... 0.9 a value is selected depending on the speed range for the type of aircraft the simulator is made at subsonic flight speeds, such as M = 0.4.

The application of the method creates simulators for different types of aircraft and spacecraft for a short period of time.

The implementation of the simulator, designed by this method, allows flights to be made, with a cabin-sized visualization of the aircraft and the surrounding area being accessible for observation from the cockpit by the monitors. The monitors are selected extremely thin to style the cabin, with a touch screen display to allow the buttons to be pressed by hand, and 3D visualization delivers greater clarity in the cabin.

3D glasses are used or glass can be made on the helmet of the pilot, such as on 3D glasses. This makes it possible to perform the same actions as when in the cabin of the aircraft. The room in which the simulator is placed is selected according to its overall dimensions. Placing a support at one end balances the structure. The control lever holder

• 4 ·· • • i • • • 4 e • • 4 a a f • • · · 4 4 4 • 4 4 « 4 · a 44 aa a * <··

The engine (s) shall be positioned and relied on by the method of spatial design of simulators during the assembly process of the simulator.

The environmental visualization system is the same for a real flight, including a map of the area that gives the pilot information about the location.

Physical condition simulators as well as the special flight simulation system are presented by sounding from amplifiers that are either connected to the panels or taken out.

Thanks to software products, flight data can be compared and even verified. With the help of the test-device used and calculated by the method, an estimation of the proper piloting technique of the pilot is also given. By comparing real flight data with that performed on the simulator, the result (estimate) is displayed. The flight data is also exported graphically for use in real flights. This is due to the design of the software part. If more than one computer is used, they all connect to cards and this allows them to work together.

The invention makes it possible to train the flight composition of proper actions in a real flight such as take-off, landing, flight in the area of the airport, etc. It also complies with the JAR (Joint Aviation Requirements) requirements for the complete formulation of aviation simulator standards and complies with the requirements of motion, visual and sound systems. The capacity of the computer, its accuracy, resolution and dynamic response are sufficient to accurately reproduce the conditions of an aviation simulator. The dynamics of the efforts of the controls reproduce those of the simulated aircraft. The visual system meets all standards. Continuous, minimum, directional visual field of view with 45 ° horizontal and 30 ° vertical field of view, as well as constant, oblique to the cockpit minimum, directional, visual field of view providing 180 ° horizontal and 40 ° vertical field of observation for each pilot . This is due to the design of the hob.

• · · ·

A sound system is also provided. Volume control

has sound level amplifiers that also meet the qualification requirements.

In addition to training purposes (such as take-off, landing, flight to the airport area, pilot training for pilots, identification of controls and emergency response), the simulator is also designed for maneuvering (combat operations). For this purpose, the structure shall be secured to the propulsion system and the overload generating device.

The use of the proposed solution has been implemented as adopted

requirements and allows both to increase the flexibility of the simulation process and to bring it very close to a real (training) flight. It is also very economical in terms of development and implementation tools.

• 9 • ·

REFERENCES · http: // www. google.bg/imgres?imgurl=http://arenalogic.eu/images/img 4515.¾ pg & imgrefurl = http: //arenalogic.eu/F16simulator.aspx&usg= dJ0kkXJiUhbNu8f NlUb7irJzxfk = & h = 300 & w ^=: 400 & sz = l 08 & hl = bg & start = 26 & zoom = l & tbnid-mBt CK-

IYx5719M: & tbnh = 93 & tbnw = l 24 & ei = nOsUT7jAFs2psgaVm8G Bw & prev ^ / searc h% 3Fq% 3Dsimulatori% 2Bna% 2BF16 ⁰ / o26start% 3D20% 26um ⁰ / o3Dl ⁰ / o26hl% 3Dbg% 26sa% 3DN % 26gbv% 3D2 ⁰ / o26tbm% 3Disch & um = l & itbs = l

2. http://www.google.com/imgres?imgurl=http://arenalogic.eu/images/Picture2.jp g & imgrefurl = http: //arenalogic.eu/Products.aspx&usg= nM3TG17RCqUuEldeStF LDT2WPzE = & h = 288 & w = ^: 432 & sz ^: = 19 & hl — bg & start ~ 127 & zoom = l & tbnid = miUXlZkvqM3pM: & tbnh = 84 & tbnw = 126 & ei-4wsUT8ylGoKOsAayg8kn & prev = / sea rch% 3Fq% 3DSimulators% 2Bna% 2Bna% 2Bna% 2Bna

16% 26start% 3D120% 26um% 3Dl% 26hl% 3Dbg% 26sa% 3DN% 26gbv% 3D2% 26tb m% 3Disch & um = l & itbs = l

3. http: // www. google. bg / imgres? imgurl = http; // www.aerosym.com/newf 16 3.jpg & imgrefurl = http: //www.aerosym.com/fl 6.html & usg = nX-

7dqXuT62R4h7MOOiPbNwlnkg = & h = 480 <fcw = 640 & sz = 62 & hl = bg & start = 54 & zoo m = l & tbnid = : BpRSi6ytzrA3BM: & tbnh: = 103 & tbnw = 137 & ei = pgsUT5PMAcWVswb ltaUr & prev = / search% 3Fq% 3Dsimulatori% 2Bna% 2BF16% 26start% 3D40% 26um% 3Dl % 26hl% 3Dbg% 26sa% 3DN% 26gbv% 3D2% 26tbm% 3Disch & um = l & itbs = l

4. http://www.google.com/imgres?imgurl=http://www.simaviatiksouth.com/Yahoo site admin / assets / images / F16 CQCPIT SIMAVIATIK.341131

430 std.jpg & imgrefurl = http.7 / www.simaviatiksouth.com / & usg = _WXfJYycPfyVCYfn0DhCRlbhAGys = & h = 542 & w = 800 & sz = 51 & hl = bg & start = 87 & zoom-l & tbnid = cG51zWkohTqbM : & tbnh = 97 & tbnw ^{::: z} 143 ^{& ei = xOsUT9aTH10AtObk2e2nAw & prev z =} / search % 3 Fq% 3DSimulators% 2Bna% 2BF16% 26start% 3D80% 26um% 3Dl% 26hl% 3Dbg% 26sa% 3DN% 26gbv% 3D2% 26tbm ° / o3Disch & um ⁼ l & itbs = l

5. http://www.google.com/imgres?imgurl=http://www.fighterpilotsusa.com/Portal s / 0 / fpusaimages / NewF16Sim.JPG & imgrefurl = http: //www.fighterpilotsusa.com/G • · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · · ··· ······· rouplncentives / F 16ViperSim / tabid / 59 / Default.aspx & usg = 0vfv51 undUztqdzGsG vCGlmBZ8c = ^: & h = ^: 277 & w = 376 & sz = 16 & hl = bg & start ^: = l 14 & zoom ^ d & kM & n3 & kMn & dM: 1 ln & 7mn & dM: 1 l & zbJ & dM: & tbnh = 90 & tbnw = 122 & ei = 0QsUT4DoK8jfsgav3MgR & prev = / searc h% 3Fq% 3Dsimulators% 2Bna% 2BF16% 26start% 3D100% 26um% 3Dl% 26hl ^o / o3Dbg% 26sa% 3DN% 26gbt% 3D & lgbt% 3D & lbb% m &lt;

6. ID Kisyov, “Material Resistance”, Sofia, 1978.

Claims (4)

(1) Semi-automated or automated computer and specialized software calculates the rudder deviations and the forces transmitted to the control lever (s) and constructs the deviation and velocity balance diagrams using known physical dependencies for the respective airplane or spacecraft with the necessary input data; 1. Method for the spatial design of flight and spacecraft simulators, including an initial stage in which the following actions are performed: 2. Method for the spatial design of simulators for aircraft and spacecraft, including a work stage in which the following actions are performed: 7), 8), 9) determining the size of the monitors and shaping the actual sizes that are obtained using formulas, tables, work with software (drawing) product to obtain each individual part of the simulator; 10) assembling virtually the entire structure of the simulator (3D space) by means of a software (drawing) product and preparing for drawing it in working drawings (2D space) according to claim 1, characterized in that the resulting virtual structure is the finished simulator, which can be drawn for working drawings in 2D space. 2) calculate the semi-automatic or automatic deviation of the rudder for steering and the effort transmitted to the pedals (the deflection of the ailerons and the forces transmitted to the control lever (s)) and construct balancing diagrams of the deviations and forces using known physical dependencies for the aircraft or spacecraft concerned with the necessary baseline data; 3. Spatial design method for flight and spacecraft simulators, including a final stage in which the following actions are performed: 11) calculations of the tensile springs for the 3D plane are made, the number of turns is calculated, the maximum stretching of the springs is calculated again, the coefficients of the springs in the space are determined and additional calculations of the springs are made; 12) in accordance with the calculations obtained, the springs are applied to the samples of the control lever (s) and pedals according to claims 1 and 2, characterized in that the results obtained make it possible to operate the springs applied to the samples of the control lever (s) and pedals only while maintaining a constant diameter. An aircraft simulator comprising a hardware part such as: at least one computer (7); a table (1) on which monitors (21) are mounted at a certain distance for reasons of the cab and which is supported by supports (13) inside and out, with the supports (13) attached to it and the floor by nuts and bolts except the lateral parts where the seat (4) passes are located only from the inside; pedals (2) that are adjustable with raised (adjuster) (14), which, when moved by pulling the adjusting lever from the cab, is fixed in the profile (12) on the hob (1) and a plate (10) is inserted into article X (11); an airplane control lever (3) through which a pedal (2) passes through the pedals (2) and is stopped by a portion of that larger diameter axle (5) which is fixedly fixed to the floor of the room; a seat (4) that moves on the axis (5) and is locked by a mechanism or a nut; a support (weight) (6) that balances the structure; engine control handle stand (8); 9 It ·· amplifiers that are either external or invisible speakers; test device (9) which compares data from two fields and is coupled to the location of the printer and the software part of the aircraft type according to claims 1 to 3, characterized in that its construction is designed in a sequential embodiment of the actions of the steps of the spatial design method for simulators for aircraft and spacecraft. An aircraft simulator comprising a hardware part such as: at least one computer (7); a table (1) on which monitors (21) are mounted at a certain distance for reasons of the cab and which is supported by supports (13) inside and out, with the supports (13) secured thereto and the circular surface (25) with nuts and bolts with the exception of the side portions where the seat (4) extends only inside; pedals (2) that are adjustable with raised (adjuster) (14), which, when moved by pulling the adjusting lever from the cab, is fixed in the profile (12) on the hob (1) and a plate (10) is inserted into article X (11); an airplane control lever (3) through which a pedal (2) passes through the pedals (2) and is stopped by a portion of that larger diameter axle (5) which is fixedly fixed to the floor of the room; a seat (4) that moves on the axle (5) and is restrained by a mechanism or a nut, with belts (28) fastened thereon and held by the holding (26) to the circular surface (25) on which the structure is mounted of a simulator constructed as a closed system; a support (weight) (6) that balances the structure; engine control handle stand (8); amplifiers that are either external or invisible speakers; tester (9) that compares data from two fields and is connected to a printer location and a propulsion system that represents two rotating rings (22) arranged perpendicular to each other, secured to supports (23) for the floor of the room; a single automatic key (27) used to shut down the drive system; an overload device (24), which is connected to the computer (s) (7) and is positioned below the circular surface (25) on which the structure and software part of the aircraft type are fixed, according to claims 1 to 4, characterized in that its construction is designed in sequential execution of I 3) comparison of the results of 1) and 2); 4) drawing up a scale-out model that reproduces the cabin of the aircraft or spacecraft type and scaling; 5) calculations of the springs used in the samples of the control lever (s) and pedals are taken, assuming the springs of radius (diameter) R (D) to be of a constant size; 6) combining the dimensions of three technological sites and creating a simulator, characterized in that the results obtained, in accordance with the JAR requirements, must correspond to those of the type of aircraft or spacecraft for which the simulator is being prepared. • «4 · • • 9 9 • 9 • • • ·· « • • · • • • · • • · • · • • · • « • · • · • • • • · ·· ·· ·· ··· ··· ···· the actions of the steps of the spatial design method for flight and spacecraft simulators.