WO2013113077A1 - 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. An aviation simulator which is intended for training pilots and is designed in accordance with the method comprises the following: a control unit (7.m, m = 1...n) with monitors (21.m, m = 1...n) 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). The field of vision corresponds to the type of craft. The aviation simulator is also suitable for a drive system (22.1 and 22.2) using a device for producing g-force (24).

Description

 METHOD OF DESIGNING SIMULATORS FOR FLIGHT

 APPARATUS AND SIMULATOR

Areas of technology

The invention relates to a method for the spatial design of a simulator for manned aircraft and spacecraft designed to train pilot-pilots and astronauts, and an aircraft simulator designed by this method, according to a specially designed desktop simulator, is intended for training pilot pilots.

Prior art

Unknown methods for the general spatial design of simulators for lethal and spacecraft.

 Known aircraft flight simulators, consisting of: at least one monitor associated with control units, which depict dashboards with a visual overview of the environment, as on some flight simulators, part of the dashboards and visualize them from projectors. Standard joysticks, through the control unit implements the control stick of the aircraft, the control knob of the engine / em and pedals [1], [2], [3].

 Other flight simulators include monitors with a picture of the surrounding space and a separate, real design for the whole cabin. The aircraft control knob, engine / s control knob and pedals are responsible for the actual dimensions, location and applied forces, as for a real aircraft [4], [5].

Well-known simulators have the following disadvantages: a stingy one-piece design due to the high complexity, the development time is very long, a design that does not generally correspond to a real aircraft cabin. The technical essence of the invention

The present invention has the purpose of solving the indicated disadvantages, as with the application of cladding methods, designing simulators for aircraft and spacecraft. The proposed method presents the opportunity for automated or semi-automated design, through specialized software and a sequence of pre-prescribed design steps. Through it, the design of simulators for various types of aircraft and spacecraft is created.

 The simulator is designed to be lightweight with reduced labor input and cost, and the general view (dashboard and view) is as close as possible or completely identical to the real one for the corresponding aircraft or spacecraft, as it is assumed that data from simulated flights are stored, processed and the results are displayed.

 The design of the flight simulator, according to the method, allows any specialist in the field of flight simulators to design one whether it independently has some type of aircraft or spacecraft or simulator, as it has enough with the input data.

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

 1) Initial stage:

 one . 1) semiautomatized or automated, using a computer and specialized software, calculates the deviations and forces transferred to the sample / s to the handle / and controls and builds balancing diagrams of deviations and forces (with respect to speed), as well as known physical dependencies are used for the corresponding aircraft or spacecraft with the following given input data, as well as additional (necessary in the process of calculating) data examined physically x dependencies that are attached when managing the controls:

G is the force applied to the control handle / s; χ _τ is the relative coordinate of the position of the transition point from the laminar to the turbulent boundary layer;

V is the maximum and minimum speed, which is divided into equal time intervals, starting from V _m j _n by V _max ;

 x is the measured distance from the cab to the movement of the control knob / s.

 1 .2) the deviations and forces transmitted to the sample / s of pedals (deviations and forces transferred to the sample / knobs / controls) are calculated semi-automatically or automatically by means of a computer and specialized software, and balancing diagrams of deviations and forces are constructed, how known physical dependencies are used for the corresponding aircraft or spacecraft with the following given input data, and additional (necessary in the calculation process) data, with the motor used physical dependencies that are applied when managing the controls:

 β is the slip angle;

V is the maximum and minimum speed, which is divided into equal time intervals, starting from V _m j _n by V _max ;

 x - the measured distance from the cab when moving the pedals and control knobs / s. When moving the control knob / s when deviating by 20 °, one should proceed from the actual dimensions of the devices.

 1 .3) comparison of results from 1 .1) and 1 .2)

 After performing calculations and constructing balancing diagrams from the samples and from the obtained calculations for the control knob / s and pedals, make the following comparison and conclusions for further actions:

1 .3.1) if the angles with the deviation of the controls increase and if the spring (s) acting on tension is used (s) in the sample (s), the handle / and the controls will be stretched (s) more. The obtained values should be larger (under tension). If the condition is fulfilled, continue the following actions (below). If not, return to t.1. 1) to correct errors and again make calculations; 1 .3.2) if the angles with the deviation of the controls decrease and therefore the springs acting during tension are used in the sample / s handle / and the controls and sample / s of the pedal will be stretched less. The obtained values should be less (under tension). If the condition is fulfilled, continue the actions in t. 1 .4) (below). If not, return to t. 1 .2) to correct the errors and again make the calculations.

 1 .4) after the computational process is completed, a real or virtual layout will be made. The layout has dimensions that can be used for various aircraft and spacecraft, so for vehicles with a double arrangement in the cockpit, the size of the seat area is doubled and the distance between them remains, in accordance with the arrangement of horizontal panels (with available devices) and a stand for the engine control knob / with aircraft and space shuttles, and with spaceships it will only triple, etc. depending on the number of astronauts. Depending on the type of aircraft and spacecraft (with one-, two-, three-seater, etc. location in the cockpit), the layout may acquire a change only in relation to its width. All other dimensions are retained to meet JAR (Joint Aviation Requirements) requirements. The simulator model is prepared on a reduced scale. In order to achieve the permissible size limits for simulators for aircraft and spacecraft, a magnifying scale is used, and the simulator performed according to the following steps is obtained on a scale of M 1: 1, according to the cockpit.

 In the calculations, deviations and efforts of the controls are saved as soon as the simulator sizes are formed (handle / controls, pedals, countertop, seat / s, axle, gravity, test-testing device, engine / s control stick stand and springs) on a larger scale. Standard sizes (some sizes of pedals, control knobs / s, seats / s, engine / s knobs, some distances for them, etc.), measured from the cab are saved.

1 .5) calculations are performed for the springs used in the sample / s of the control knob / s and the sample / s of the pedals to accept permissible size limit on the diameter D of springs of constant size [6].

 When controlling the control knob / s and pedals, cylindrical coil springs with small pitch are selected that will work under tension.

 From the results obtained for controls (handle / control and pedals), the same stiffness is selected and the dimensions for each spring are drawn. The diameter adopted for structural reasons is initially taken on an increasing scale, as a constant value for all springs attached to the control knob / s and pedals, and then makes a choice on a scale of 1: 1, the diameter is again a constant value for all springs applied to control knob / s and pedals.

 1 .6) combined dimensions are drawn up at three technological facilities and a simulator is created:

 16. 1) on the simulator layout on a reduced scale;

 1 .6.2) on an aircraft or spacecraft;

 1 .6.3) on computer equipment (monitor).

 If you perform the following steps, you will get the dimensions of the simulator, the dimensions of the panel in the cockpit and the distance from the eyes of the pilots to the fan or to the ceiling of the cockpit.

 2) An intermediate step, including:

 2. 1) after ensuring the necessary dimensions, proceed to:

 2.1. 1) dividing the panels into a certain number of monitors;

2. 1 .2) are calculated by the formulas: coefficient - R _n ; total coefficients - R _zy , R _xy , R _xz ; coefficient determining the size of monitors (for the choice of monitors) - R ₀ 6mo; coefficients for reducing the size of the simulator in the plane zy, xy, z - R _CZ y, Rcxy, cxz ^

R _n = MM / TC

 MM - monitor layout sizes;

TS - dimensions of the panel of an aircraft or spacecraft

Rxy = Rnx + R _ny for n = 1, 2, 3, 4

Rnx, Rn, Rnz - coefficients equivalent to R _n , no with respect to the x, y, z axis;

 n - number of monitors, relative to the location:

 1 - main monitor (s)

 2 - horizontal monitors

 3 - vertical monitors

 4 - monitor (s) located above the vertical and main (s) monitors

R _zy , R _X y, R _xz; - total coefficients in the Ozy fields,

Oh, Oxz

Rczy ^- Rz / 2, cxy ^~ y / 2, R _cxz - R _X z / 2

 Rz, Rxy, z - total coefficients in the Ozy fields,

Oh, Oxz.

Knowledges FOR R _n ; R _zy , R _xy , R _xz ; R ₀ 6 _U K ;; Rczy, Rcxy, Rcxz are used to execute simulator drawings in 2D and 3D spaces, transfer a project in space, determine size limits, determine the size and number of monitors and its virtual assembly. The results from the formulas are entered into the table for each field Ozy, Ohu, Oxz.

 1 .2.3) the choice of monitors is made. It is advisable to use 3D LCD touch screen display, exceptionally thin monitors. It can be taken either only 2D or only 3D. Due to the limited number of 3D monitors, those that are converted can be selected.

 The results for the panel are entered in a table where the panel view, types of monitors, monitor number, width, height, diagonal and base are recorded.

 When choosing monitors, take into account the distance from the pilot's eye to the fanlight or to the ceiling of the cockpit.

2.2) after selecting the monitors, axonometric drawings are prepared in triplicate, in relation to the three coordinate fields Ozy, Ohu, Oxz. Draw on them the size of the simulator in increasing scale and size limits (sizes from t.1 .2)) applied with coefficients R _czy , Rc y, Rc xz in fields with increasing scale.

 2.3) from the parameters obtained by the constructive method, the actual dimensions are selected. Actual dimensions are taken from limit sizes from allowable limits. They can be reduced below the limit, only in accordance with the design and the cabin. Spatial drawings are made for this type of isometry, like NE Isometric for components. Then the entire simulator is compiled virtually on software.

 2.4) the simulator obtained in this way is defined as acceptable in accordance with its actual dimensions in 3 D space and drawings of the real simulator in 2D are made, with the exception of the spring drawings.

 3) The final stage, including:

 3.1) spring calculations are performed for the 3 D plane with the following input data:

P _m in - minimum load applied to the control knob / s and pedals;

 RT is the maximum load applied to the control knob / s and pedals;

 x - coordinates of the deviation of the controls;

 G - module of angular deformation with spring steel St70;

Oh, that. - allowable shear stress;

 R (D) is the reduced radius (diameter) of the simulator spring for the aircraft and spacecraft in M l: l. R (D) is a constant value for all springs applied to simulators for aircraft and spacecraft in step 3) on a scale of M 1: 1.

3.1. 1) the maximum torque M _{mustache is} calculated;

 3.1 .2) the maximum spring tension max f is calculated;

3.1 .3) the maximum tangential stress of maxt _{x is} checked for a set section of pure torsion max τ _χ <

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

 3.1.3.2) the number of active windings i is calculated;

3. 1 .3.3) the result from the number of active windings i is recorded; 3.1.3.4) springs are selected.

3.1.4) the minimum light opening is calculated 6 _m j „;

 3.1.5) the initial light opening δο is calculated;

3.1.6) the initial (free) length L _{0 is} calculated;

3.1.7) the length after loading max P L _{2 is} calculated;

 3.1.8) the length after load min P Li is calculated;

3.1.9) spring lengths are calculated under tension fi and f ₂ ;

 3.1.10) the helix angle a is calculated:

3.1.10.1) the spring pitch h is calculated and the dimensions d, D, δ ₀ , Lo and i of the springs are recorded.

 3.1.11) the length of the helix 1 is calculated;

 3.1.12) the spring constant c is calculated;

 3.1.13) in accordance with the distances that are obtained when arranging the dimensions of the samples on the handle / and the control and pedal, the number of winding i is selected;

 3.1.14) the repetition is performed on t.1.1.1), t.3.1.2), t.3.1.3) and t.Z.1.3.1);

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

 When a spring is transferred from 3D to 2D space, changes occur that are reflected in the working drawings.

In order to use the Oxyz coordinate system, the coefficient k _zy , k _xy , k _xz . _Is determined for each field. The coefficients k _zy , k _xy , k _{xz are} equivalent to (k). For each maximum spring tension max f, with respect to the length after the load minP Li and the number of windings i, the necessary space coefficient is taken for all Ozy fields,

Oh, OXZ, ACCORDINGLY with Coefficients R _CZ y, Rcxy, Rcxz from t.2.1) and is written according to the coordinate system Oxyz.

 Then the springs are calculated to take the acceptable value of the coefficient for the springs in space (k), multiplied by the coefficient at maximum spring tension. Those. (k) * max f.

3.1.16) from the maximum tension of the springs max f is the coefficient for a spring in space: 3.1.16.1) divide the previous maximum stretches max f by the coefficients to reduce the size of the simulator in the field zy, xy, xz, i.e. on R _czy , R _cxy , R _cxz ;

 3.1.16.2) from t.1.1.15) are taken newly received maximum spring tension max f;

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

 3.1.16.4) we obtain the coefficients for the springs in the space (k) for each field Ozy, Ohu, Oxz.

 The location of the springs is determined in which field the action is performed and what coefficient will be used. The following additional calculations are made that will determine the operation of the controls (knobs / controls and pedals), i.e. spring work.

 3.1.17) springs are selected;

3.1.18) the values of the minimum light opening 8 _tp1 are taken from t.3.1.4);

 3.1.19) additional calculations of the initial light hole δο are performed;

 3.1.20) additional calculations of the initial (free) length Lo are performed;

3.1.21) additional calculations of the length after the load max P L ₂ are performed according to the formula:

L ₂ = Lo + max f + (k) * max f

 3.1.22) additional length calculations are performed after the load min P Li;

3.1.23) additional calculations of the length of the springs under tension f) and f ₂ are performed;

3.1.23.1) for r- ;; 3.1.23.2) for f ₂ .

 3.1.24) additional calculations of the helix angle a are performed:

 3.1.24.1) additional calculations of the spring pitch h are performed:

The dimensions of the springs are described as: d, D, δο, Lo, i. 3.1 .25) additional calculations are performed for the length of the helix 1;

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

 c = max P / (max f + (k) * max f)

 3.2) compares the calculated sizes from t.3. 1) springs with maximum capabilities corresponding to the sizes that are determined from the actual sizes of the sample / handles of the handle / control and sample / pedals of the pedals, if the dimensions obtained during the calculation do not correspond, return to point 3. 1), and if the dimensions obtained during the calculation correspond, therefore, the results obtained for the dimensions of the springs are set as final in the drawings for the sample / handles / control knobs and sample / pedals and the remaining drawings that are not fulfilled in Section 2.4) are performed.

 The flight simulator is designed by the spatial design method of flight simulators for aircraft and spacecraft and consists of at least one control unit. A worktop that is supported by supports inside and out. The supports are fixed to it and to the floor motionless. Only the side parts from the countertop where the seats pass do not fasten with supports outside. Monitors are placed on it at a certain distance for reasons of distance in the cockpit of the aircraft. The dimensions of the whole structure are obtained according to the method for the spatial design of simulators.

 Devices in the cabin for a visual overview of the surrounding space are displayed on monitors, as follows:

 1) the front panel monitor includes instruments in the cockpit from the front panel of the aircraft and a visual overview of the surrounding area, i.e. area in which flights are operated;

 2) monitors depicting side panels (vertical and horizontal), including instruments in the cabin from the horizontal panels of the aircraft and cash devices in the cabin from the vertical panels of the aircraft, together with a visual overview of the surrounding space.

Pedals attached to countertops are adjustable. Their regulation is carried out from the lift (regulator), which pulls them after pulling the handle to adjust the cab. On the countertop, the profile is formed, where the elevator (regulator) with pedals is attached, as they are fixed with the bracket of the product X mounted in the countertops and adhere to this method.

 The control handle of the aircraft, through which the axis passes, fixing the control handle through the foot, is connected from the pedals motionless to the floor of the room. The seat is movable. It moves along the axis and is locked by a mechanism or nut. The axis is fixed to the countertop motionlessly at one end, and at the other end - with support (weight).

 The airplane control handle equipped with springs, pedals also equipped with springs and the engine control handle represents joysticks that are connected to the control unit / s, so for the aircraft control handle the corresponding joystick is taken and connected with the sample, for the engine control stick - the joystick is placed on the stand, and pedals with a lift (regulator) are connected to the control unit / s.

 The noise in the desktop simulator published by the engine comes from an amplifier with thin columns. They are carried out or the so-called invisible speakers that are built into the monitors are used.

 Flight data and settings that are performed are included in the embedded program in the control unit (s). To the control unit associated with the monitor depicting the main panel is connected to a test-testing device in place of the printer.

Explanations (descriptions) on applied figures

The invention will be better explained using the following description of the method for the spatial design of simulators for aircraft and spacecraft and an aircraft simulator, according to the method and its parts with reference to the accompanying figures, in which:

 figure 1 is an axonometric view of the layout obtained in step 2); figure 2 is a top view of the layout according to FIG. one ;

 figure 3 is a perspective view of an aircraft simulator;

figure 4 is a main view of the simulator, according to fig. 3; figure 5 is a top view of the simulator, according to fig. 3;

 figure 6 is a rear view of the simulator, according to fig.Z;

 FIG. 7 is a perspective view on a large scale of a mechanism that locks the seat and can be used in place of the nut, according to FIG. 3;

 figure 8 is a perspective view on a large scale of a special key that is used to open the mechanism for the seat stopper, according to Fig.7;

 figure 9 is a diagram of a simulator with a single location in the cabin, according to fig. 3;

 figure 1 0 is a diagram of a simulator with a double arrangement in the cabin, according to Fig.9;

 figure 1 1 is a perspective view of a simulator with a single location in the cab with a drive system and a device for creating overload, according to fig.Z;

 FIG. 12 is a perspective view of a simulator with a double arrangement in a cab with a drive system and a device for creating overload, according to FIG. P .

Examples of the invention

The method for the spatial design of simulators for aircraft and spacecraft is explained using the following exemplary implementation without limitation:

Example Ns l:

 The method is developed according to the invention regarding aircraft of military aviation. The method is as follows:

 1) Initial stage:

For aircraft of military aviation, the method sequence is used, as the first two stages are performed for aircraft from military aviation with the corresponding given input data, and additional (necessary in the process calculation) of data, with inspection of the used physical dependencies that are applied when managing the controls.

 1 .3) comparison of results from t. 1. 1) and t. 1.2)

 After performing the calculations and constructing balancing diagrams from the samples and from the obtained calculations for the control knob / s and pedals, make the following comparisons and conclusions for further actions:

 13. 1) if the angles during deviation of the controls are increased and if the spring (s) acting on tension is used (s) in the sample (s), the handle / and the controls will be stretched (s) more. The values obtained should be larger (under tension). If and the condition is fulfilled, continue the following actions (below). If not, return to t. 1. 1) to correct errors and make calculations again;

 1 .3.2) if the angles during the deviation of the controls decrease and consequently the springs acting under tension are used in the sample (s) of the handle / and the controls and sample (s) of the pedal will be stretched less. The obtained values should be less (under tension). If the condition is fulfilled, continue actions in t. 1 .4) (below). If not, return to t. 1 .2) to correct the errors and do the calculations again.

1 .4) after the computational process is completed, a real or virtual layout is prepared from. The layout for military aircraft with a single location in the cockpit is similar to that in FIG. 1 and 2. When double occupancy in the cab, the distance from the area for the location of the seat double. Depending on the type of aircraft (with a single and double seat in the cockpit), the layout can only get a change in relation to its width. All other dimensions are retained to meet JAR (Joint Aviation Requirements) requirements. The simulator model is being prepared on a reduced scale. In order to achieve the permissible boundary size of simulators for military aircraft, an increasing scale is used, and the simulator performed according to the following steps is obtained in a scale of M 1: 1, corresponding to the cockpit. In the calculations, deviations and efforts of the controls are saved as soon as the simulator's dimensions (handle / controls, pedals, tabletop, seat / axle, gravity, test-testing device, engine / s control stick stand and springs) increase in scale. Standard sizes (some sizes of pedals, control knobs / s, seats / s, engine / s knobs, some distances for them, etc.), measured from the cab are saved.

 1 .5) calculations are performed for the springs used in the trimmer / s of the control knob / s and of the pedal sample / s for accepting the permissible boundary size for the diameter D on the springs of constant size [6].

 When operating on the control knob / s and pedals, cylindrical coil springs with small pitch are selected that will work under tension.

 From the results obtained for controls (handle / control and pedals), stiffness is selected and dimensions for each spring are drawn. The diameter adopted for structural reasons is initially taken on an increasing scale, as a constant value for all springs attached to the control knob and pedals, and then makes a choice on a scale of 1: 1, diameter is a constant value for all springs attached to the control knob and pedals .

 1 .6) combined dimensions are drawn up at three technological facilities and a simulator is created:

 16. 1) on the simulator layout on a reduced scale;

1 .6.2) on an aircraft of military aviation;

 1 .6.3) on computer equipment (monitor).

 If you perform the following steps, then you will get the dimensions of the simulator will provide the dimensions of the panel in the cockpit and the distance from the eyes of the pilots to the fan.

 2) An intermediate step, including:

 2.1) after ensuring the necessary dimensions, proceed to:

 2.1. 1) dividing the panels into a certain number of monitors;

2. 1 .2) are calculated by the formulas: coefficient - R _n ; total coefficients - R _zy , R _xy , R _xz ; coefficient determining monitor sizes (for selecting monitors) - R ₀ 6m ₀ ; coefficients for reducing the size of the simulator in the plane zy, xy, xz - R _CZ y, cxy, cz ^

R _n = MM / TC

 MM - monitor layout sizes;

TS - dimensions of the panels of an aircraft of a military aircraft

R * _y = R _nx + Rny for n = 1, 2, 3, 4

Rnx, ny, R _nz - coefficients equivalent to R _n , no with respect to the x, y, z axis;

 n - number of monitors, relative to the location:

 1 - main monitor (s)

 2 - horizontal monitors

 3 - vertical monitors

 4 - monitor (s) located above the vertical and primary monitors

Rc-bshcho ⁼ (Rzy + Rxy + R _xz ) / 3

R _zy , R _xy , R _xz - total coefficients in the Ozy fields,

Oh, Oxz

Rczy ^- Rz I; Rc ^- Rx I 2, Rcxz ^- R z I 2

R ₂ y, R _xy , R _xz - total coefficients in the Ozy fields,

Oh, Oxz.

The obtained values for R _n ; R _zy , R _xy , R _xz ; R _{o 6} m ₀ ; Rczy, Rcxy _? Rcxz are used to execute simulator drawings in 2D and 3D spaces, transfer a project in space, determine boundary dimensions, determine the size and number of monitors and its virtual assembly. The results from the formulas are entered into the table for each field Ozy, Ohu, Oxz.

2. 1 .3) the choice of monitors is made. It is advisable to use 3 D LCD touch screen display, exceptionally thin monitors. May be taken either only 2D or only 3 D. Due to the limited number of 3D monitors, those that are converted can be selected.

 The results for the panel are entered in a table where the panel view, types of monitors, monitor number, width, height, diagonal and base are recorded.

 When choosing monitors, take into account the distance from the pilot's eye to the fan.

2.2) after selecting the monitors, prepare axonometric drawings in triplicate, with respect to the three coordinate fields Ozy, Okhu, Oxz. The simulator sizes on an increasing scale and the limiting sizes (sizes from t. 1 .2)) applied with the coefficients _czy , R _CX y, Rcxz in fields with increasing scale are applied to them.

 2.3) from the parameters obtained by the constructive method, the actual dimensions are selected. Actual dimensions are taken from the limit sizes from the allowable limits. They can be reduced below the limit, only in accordance with the design and the cabin. Spatial drawings are made for this type of isometry, like NE Isometric for components. Then the entire simulator is compiled virtually on software.

 2.4) the simulator thus obtained is defined as acceptable in its actual size in 3 D space and drawings of the real simulator in 2D are made, with the exception of the spring drawings.

 3) The final stage, including:

 3.1) Spring calculations are performed for the 3D plane with the following input data:

 Pmin - minimum load applied to the control knob / s and pedals;

 Mouth - maximum load applied to the control knob / s and pedals;

 x - coordinates of the deviation of the controls;

G - module of angular deformation with spring steel St70; t _D op. - allowable shear stress;

R (D) is the reduced radius (diameter) of the simulator spring for the aircraft in M l: 1. R (D) constant for all springs used for flight simulators for military aircraft in stage 3) on an M1: 1 scale.

3.1.1) the maximum torque M _{usb is} calculated;

 3.1.2) the maximum spring tension max f is calculated;

3.1.3) the maximum tangential stress of the ottomans _{x is} checked for a set section of pure torsion max τ _χ <

3.1.3.1) the cross-sectional diameter d is calculated;

3.1.3.2) the number of active windings i is calculated;

3.1.3.3) the result from the number of active windings i is recorded;

 3.1.3.4) springs are selected.

3.1.4) the minimum light opening is calculated 6 _m j _n ;

 3.1.5) the initial light opening δο is calculated;

3.1.6) the initial (free) length L _{0 is} calculated;

3.1.7) the length after loading max P L _{2 is} calculated;

 3.1.8) the length after load min P Li is calculated;

3.1.9) spring lengths are calculated under tension fi and f ₂ ;

 3.1.10) the helix angle a is calculated:

 3.1.10.1) the spring pitch h is calculated and the dimensions d, D, δο, Lo and i of the springs are recorded.

 3.1.11) the length of the helix 1 is calculated;

 3.1.12) the spring constant c is calculated;

 3.1.13) in accordance with the distances that are obtained when arranging the dimensions of the samples on the handle / and the control and pedal, the number of winding i is selected;

 3.1.14) the repetition is performed on t.1.1.1), t.3.1.2), t.3.1.3) and t.Z.1.3.1);

 3.1.15) at the selected values of the quantity on the active windings i, the maximum spring tension max f is calculated again.

 When a spring is transferred from 3D to 2D space, changes occur that are reflected in the working drawings.

In order to use the Oxyz coordinate system, the coefficient k _zy , k _xy , k _{xz is} determined for each field. The coefficients k _zy , k _xy , k _{xz are} equivalent to (k). For each maximum spring tension max f, in relation to the length after the load minP L _\ and the number of windings i, the necessary coefficient of space is taken for all fields Ozy, Oxu, Oxz, in accordance with the coefficients R _czy , R _C x, Rcxz from t. 2. 1) and written in the coordinate Ohug system.

 Then, the springs are computed to take the acceptable value of the coefficient for the springs in the space (k), multiplied by the coefficient at maximum spring tension. Those. (k) * max f.

 3.1. 16) from the maximum tension of the springs max f is the value of the coefficient for the spring in space:

3.1. 16. 1) divide the previous maximum tensile max f by coefficients to reduce the size of the simulator in the field zy, xy, xz, i.e. on R _czy , R _cxy , R _{c xz} ;

 3. 1. 16.2) from t.3 .1.1 5) the newly acquired maximum spring springs max f are taken;

3.1 .16.3) the newly obtained maximum stretches max f are multiplied by the coefficients of reducing the size of the simulator in the field zy, xy, xz, i.e. on R _czy , R _{C) iy} , R _cxz ;

 3. 1 .16.4) we obtain the coefficients for the springs in the space (k) for each field Ozy, Ohu, Oxz.

 The location of the springs is determined in which field the action is performed and what coefficient will be used. The following additional calculations are made that will determine the operation of the controls (knobs / controls and pedals), i.e. spring work.

 3.1. 17) springs are selected;

 3.1. 1 8) the values of the minimum light opening δηι ι η are taken from t.3.1.4);

 3.1. 19) additional calculations of the initial light hole δο are performed;

 3.1 .20) additional calculations of the initial (free) length Lo are performed;

3.1 .21) additional calculations of the length after the load max P L ₂ are performed according to the formula:

L ₂ = Lo + max f + (k) * max f

3. 1 .22) additional length calculations are performed after the load min P L i; 3.1 .23), additional calculations of the length of the springs under tension f | and f ₂ ;

3.1.2. 1) for r ^" ,; 3.1 .23.2) for f ₂ .

 3.1 .24) additional calculations of the angle of inclination a of the helix a are performed:

 3.1 .24.1) additional calculations of the spring pitch h are performed:

The sizes of the springs are described, for ak: d, D, δο, L ₀ , i.

 3. 1 .25) additional calculations are performed the length of the helix 1;

 3.1.26), additional calculations of the spring constant are performed with the formula:

 c = max P / (max f + (k) * max f)

 3.2) compares the calculated sizes from t.3.1) of the springs with the maximum capabilities corresponding to the sizes that are determined from the actual sizes of the sample / handles of the handle / control wheels and the sample / pedals of the pedals, if the sizes obtained during the calculation do not correspond, return to t.3 . 1), and if the dimensions obtained during the calculation correspond, therefore, the results obtained for the dimensions of the springs are set as final in the drawings for the sample / handles / control knobs and sample / pedals and the remaining drawings that are not fulfilled in Section 2.4) are performed.

Example N ° 2:

 The method is developed according to the invention relating to spacecraft. The method is as follows:

 1) Initial stage:

 For spacecraft, the method sequence is used according to Example N ° l. The first two actions are performed for spacecraft with the corresponding given input data, as well as additional (necessary during the calculation) data, with an examination of the physical dependencies used, which are applied when controlling the controls.

1 .3) In action 1 .3) the number of samples on the control handle and the number of samples of the pedals are considered. 1 .4) After the computational process is completed, a real or virtual layout will be made. A spacecraft layout similar to this one with two local locations in the cockpit. The distance of the area for the location of the seat is doubled, in accordance with the location of the horizontal panels (with cash devices) and the stand for the engine / her control knob for space shuttles, and for spaceships only triple, etc. depending on the number of astronauts. The layout only changes in relation to its width. All other dimensions are retained to meet JAR (Joint Aviation Requirements) requirements. The simulator model is being prepared on a reduced scale. In order to achieve the acceptable boundary dimensions of the simulators for spacecraft, a magnifying scale is used, and the simulator performed according to the following steps is obtained on a scale of M 1: 1, according to the cockpit.

 In the calculations, deviations and efforts of the controls are saved as soon as the simulator sizes are formed (control knobs, pedals, tabletop, seats, axle, gravity, test-testing device, engine control knob stand and springs) on an increasing scale. Standard sizes (some sizes of pedals, control knobs, seats, engine control knobs, some distances for them, etc.), measured from the cab, are protected.

 1 .5) In action 1.5) the number of samples on the control handle and samples of pedals, respectively, and springs are considered. When using similar samples for the control knob and for the pedals, they are applied for each similar sample (for the control knob and for the pedals) calculated by the similar method of springs.

 1 .6) Action 1 .6) is performed according to the method according to the example \ for spacecraft.

 2) An intermediate step, including:

 In the intermediate stage, the number of monitors, which is different, is considered.

 3) The final stage, including:

In the final stage, according to the number of samples, the number of springs is determined. When using similar samples for a pen controls and for pedals are applied for each similar sample (for the control knob and for pedals), calculated by a similar method of springs.

Example MOH:

 The method is developed, according to the concept of civil aviation aircraft. Method d is as follows:

 1) Initial stage:

 For civilian aircraft, the method sequence is used according to Example l. The first two actions are performed for civil aviation aircraft with the corresponding given input data, as well as additional (necessary during the calculation) data, with the inspection of the physical dependencies used, which are applied when controlling the controls.

 1 .3) In action 1 .3) the number of samples on the control handle and the number of samples of the pedals are considered.

 1 .4) After the computational process is completed, a real or virtual layout will be made. The model for civil aviation aircraft is a model for double-seat vehicles in the cockpit. The distance of the area for the location of the seat is doubled and the distance between them remains, in accordance with the arrangement of horizontal panels (with available devices) and the stand of the engine control knob. The layout only changes in relation to its width. All other dimensions are retained to meet JAR (Joint Aviation Requirements) requirements. The simulator model is being prepared on a reduced scale. In order to achieve the permissible boundary size of simulators for civilian aircraft, an increasing scale is used, and the simulator performed according to the following steps is obtained on a scale of M 1: 1, according to the cockpit.

In the calculations, deviations and efforts of the controls are saved as soon as the simulator sizes are formed (control knobs, pedals, countertop, seats, axle, gravity, test-testing device, engine control knob stand and springs) in the increased scale. Standard sizes (some sizes of pedals, control knobs, seats, engine control knobs, some distances for them, etc.) measured from the cab are protected.

 1 .5) In action 1 .5) the number of samples on the control handle and samples of the pedals, respectively, and springs are considered. When using two similar samples for the control handle and two for the pedals, they are applied for each similar sample (for the control handle and pedals), calculated by the similar method of springs.

 1 .6) Action 1 .6) is performed according to the method according to the example of Ne l for civilian aircraft.

 2) An intermediate step, including:

 In the intermediate stage, the number of monitors, which is different, is considered.

 3) The final stage, including:

 In the final stage, according to the number of samples, the number of springs is determined. When using two similar samples for the control knob and two for the pedals, they are applied for each similar sample (for the control knob and for the pedals), calculated by the similar method of springs.

Example N ° 4:

 The method is developed according to the invention regarding helicopters. The method is as follows:

 1) Initial stage:

 For helicopters, the sequence of the method is used, according to the example \. The first two actions are performed for helicopters with the corresponding given input data, as well as additional (necessary during the calculation) data, with an examination of the physical dependencies used, which are applied when controlling the controls.

 1 .3) In action 1 .3) the number of samples on the control handle and the number of samples of the pedals are considered.

1.4) After the computational process is completed, a real or virtual layout will be made. Model for helicopters with single arrangement in a cabin similar to that in FIG. 1 and 2. With a double occupancy in the cab, the distance of the area for seating is doubled. Depending on the type of helicopter (with a single and double seat in the cockpit), the layout may only change with respect to its width. All other dimensions are retained to meet JAR (Joint Aviation Requirements) requirements. The simulator model is being prepared on a reduced scale. In order to achieve the permissible boundary dimensions of the simulators for helicopters, a magnifying scale is used, and the simulator performed according to the following steps is obtained on a scale of M 1: 1, in accordance with the cabin.

 In the calculations, deviations and efforts of the controls are saved as soon as the simulator sizes are formed (handle / controls, pedals, countertop, seat / s, axle, gravity, test-testing device, engine / s control stick stand and springs) on a larger scale. Standard sizes (some sizes of pedals, control knobs / s, seats / s, engine / s control knobs, some distances for them, etc.), measured from the cab are saved.

 1 .5) In action 1 .5) the number of samples on the control handle and samples of the pedals, respectively, and springs are considered. When using similar samples for the control knob and for the pedals, they are applied for each similar sample (for the control knob and for the pedals) calculated by the similar method of springs.

 1 .6) Action 1 .6) is performed according to the method according to the example of Ne l for helicopters.

 2) An intermediate step, including:

 In the intermediate stage, the number of monitors, which is different, is considered.

 3) The final stage, including:

In the final stage, according to the number of samples, the number of springs is determined. When using similar samples for the control knob and for the pedals, they are applied for each similar sample (for the control knob and for the pedals) calculated by the similar method of springs. Example N ° 5:

 The method was developed according to the acquisition regarding aircraft of light aviation. The method is as follows:

 1) Initial stage:

 For light aircraft, the method sequence is used according to example j ° l. The first two actions are performed for aircraft of light aviation with the corresponding given input data, as well as additional (necessary in the process of calculating) data, with an examination of the physical dependencies used, which are applied when controlling the controls.

 1 .3) In action 1 .3) the number of samples on the control handle and the number of samples of the pedals are considered.

 1 .4) After the computational process is completed, a real or virtual layout will be made. The layout for single-seat aircraft in light aircraft is similar to that in FIG. 1 and 2. With a double occupancy in the cab, the distance of the area for seating is doubled. Depending on the type of aircraft (with a single or double location in the cockpit), the layout may only change with respect to its width. All other dimensions are retained to meet JAR (Joint Aviation Requirements) requirements. The simulator model is being prepared on a reduced scale. In order to achieve acceptable boundary sizes of simulators for light aircraft, an increasing scale is used, and the simulator performed according to the following steps is obtained on a scale of M 1: 1, in accordance with the cockpit.

 In the calculations, deviations and efforts of the controls are saved as soon as the simulator sizes are formed (handle / controls, pedals, countertop, seat / s, axle, gravity, test-testing device, engine / s control stick stand and springs) on a larger scale. Standard sizes (some sizes of pedals, control knobs / s, seats / s, engine / s control knobs, some distances for them, etc.), measured from the cab are saved.

1 .5) In action 1 .5) the number of samples on the control handle and samples of the pedals, respectively, and springs are considered. At using similar samples for the control stick and for the pedals are applied for each similar sample (for the control stick and for the pedals), calculated by a similar method of springs.

 1 .6) Action 1 .6) is performed according to the method according to Example N »l for aircraft of light aviation.

 2) An intermediate step, including:

 In the intermediate stage, the number of monitors, which is different, is considered.

 3) The final stage, including:

 In the final stage, according to the number of samples, the number of springs is determined. When using similar samples for the control knob and for the pedals, they are applied for each similar sample (for the control knob and for the pedals) calculated by the similar method of springs.

Options for performing the simulator by the method of spatial design of simulators for aircraft and spacecraft are explained using the following examples:

Example N26:

For simulators for spacecraft (Fig. 10), a change occurs during the design of the countertop (1) - it is designed wide, due to the use of a double or triple, etc. location. The location of the stand for the engine control knob (8) depends on the type of apparatus. The control knob (3) is also supplied in accordance with the arrangement. The sample is the same. A connection of similar samples of the control handle is used (Z.t, t = 1 ... p). The dimensions (D) of the springs (29.1 .Ϊ, i = 1, 2) are stored as a constant value. There is no change in the sample pedals (2), as well as the sizes (D) of the springs (29.2.j, j = 1, 2). Their number changes (similar samples are used, which are not interconnected like a control knob (3) because computational work is complicated) and sizes, in accordance with calculations. Linking the samples to the control unit (s) enables the samples, both the control knob (Z.t, t = 1 ... p), and the pedals (2.m, t = 1 ... p) to perform joint movements, for example, one sample of the control knob (3.1) with a deviation in this the other control knob (3.2) deviates in the same direction, etc. The number and size of monitors (21. M, m = 1 ... p) varies depending on the calculations. The test-testing device (9) does not change in design. The only change is in the number of recorders. A change in the seat structure (4) occurs when using a coupled structure on similar seats (4.t, t = 1 ... n), as between them, depending on the type of spacecraft, a monitor is placed (with available instruments) and depending from the location of the engine control knob, a stand is designed for it or tripled, etc. , according to the number of astronauts. With the mechanism (30.0) of FIG. 7 and the nut (30), the retaining structures on similar seats (4.m, t = 1 ... p), changes in dimensions occur, in accordance with the axis (5). The axis (5) passes again through the countertop (1). The connection of the control handles (Z.t, t = 1 ... p) and the connection of the seats (4.t, t = 1 ... p) is supported by the support (weight) (6). For support (gravity) (6), when changes occur in size, its weight changes. This is consistent with the simulator obtained when performing the calculations. A visual overview of the panels and the surrounding space is consistent with the appearance of the apparatus and implemented according to methods known in the art.

When using the drive system (22.1 and 22.2) (Fig. 12), the circuit of Fig. 10 (applicable to space shuttles) is constructed as a closed system of monitors (21. M, m = 1 ... P) and is fixed motionless for a circular surface (25) for the drive system itself (22. 1 and 22.2). The drive system (22.1 and 22.2) represents two rotating rings (22. 1 and 22.2) located perpendicular to each other, mounted on racks (23. 1 and 23.2) to the floor of the room. To stop it, use a single automatic key (27). Seats (4.m, m = 1 ... n) are designed integrally downward. They are equipped with belts (28. m, m = 1 ... p) for holding astronauts. After moving the seats (4.m, m = Ι.,. Η), the holder (26) is placed in the cabin, which supports them to the circular surface (25). A circular surface (25) is fixed for the rotating rings (22. 1 and 22.2) on the drive system. A device for creating an overload (24) is supplied under the circular surface (25), which is connected with the control unit / s (7.m, m = 1 ... p). The design of FIG. 12 is also applicable to spacecraft (spacecraft) with an increase in the width of the tabletop for the installation of additional seats and calculated monitors.

Example N ° 7:

 For simulators of civilian aircraft, a design similar to these spacecraft with a double arrangement in the cockpit is used (Fig. 10), with the only difference in size. Only the sizes (D) of the springs (29.1 l, i = 1, 2 and 29.2.j, j = 1, 2) keep a constant value. A visual overview of the panels and the surrounding space is consistent with the appearance of the apparatus and implemented according to methods known in the art. The simulator is not attached to the drive system (22.1 and 22.2), to which the device for creating overload is attached (24).

Ne8 example:

 For helicopter simulators, the design is used both for helicopters with a single location in the cockpit (using the design of an aircraft simulator designed according to the method) (Fig. 3, Fig. 9), and with a double (similar to these spacecraft, but without installing horizontal monitors ( 21 .m, m = Ι.,. Η) between the seats (4.m, m = Ι.,. Η)) (Fig. 12), with the only difference in size. Only the dimensions (D) of the springs (29.1 .i, i = 1, 2 and 29.2J, j = 1, 2) keep a constant value. A visual overview of the panels and the surrounding space is consistent with the appearance of the apparatus and implemented according to methods known in the art. Depending on the purpose of the helicopter, the simulator can also be attached to the drive system (22. 1 and 22.2), to which the device for creating overload (24) is attached (Fig. 1 1, Fig. 12).

Example N ° 9:

For light aviation, single-seaters with aircraft pilots located to each other are used. For a two-seater arrangement in the cockpit, a design similar to these spacecraft, but without installation on horizontal monitors (21. M, t = 1 ... p) between the seats (4.m, m = l ... n) (Fig. 12), with the only difference in size. Only the sizes (D) of the springs (29.1.i, i = 1,2 and 29.2.j, j = 1,2) keep a constant value. A visual overview of the panels and the surrounding space is consistent with the appearance of the apparatus and implemented according to methods known in the art.

 For aircraft with a single location in the cockpit, the design of an aircraft simulator, designed according to the method, is used as a change in size (Fig. 3, Fig. 9). Only the sizes (D) of the springs (29.1.i, i = 1,2 and 29.2.j, j = 1,2) keep a constant value. A visual overview of the panels and the surrounding space is consistent with the appearance of the apparatus and implemented according to methods known in the art.

 For trikes, a change in design occurs in the number of monitors (21. m, t = 1 ... p): three monitors are used (21. ha, m = 1 ... 3), a control knob (3) (makes a trapezoid, which pulled by a spring) and the width of the countertop (1). There is a change in size. Only the dimensions (D) of the springs (29.2.j, j = 1,2) of the pedals and this trapezoid keep a constant value. A visual overview of the panels and the surrounding space is consistent with the view of a motor hang glider and implemented according to methods known in the art.

 Depending on the purpose of the aircraft, the simulator can also be attached to the drive system (22.1 and 22.2), to which the device for creating overload (24) is attached (Fig. 11, Fig. 12).

NelO example:

For military aviation, single-seaters with aircraft pilots located to each other are used. When located to each other, the design is similar on these spacecraft, but without installation on horizontal monitors (21. m, t = 1 ... p) between the seats (4.t, t = 1 ... p) (Fig. 12), with the only size difference. Only the dimensions (D) of the springs (29.1 l, i = 1,2 and 29.2.}, J = 1,2) keep a constant value. A visual overview of the panels and the surrounding space is consistent with the appearance of the apparatus and implemented according to methods known in the art. For single-seat aircraft, the design of an aircraft simulator designed according to the method as a change in size (Fig. 3, Fig. 9) is used. Only the sizes (D) of the springs (29.1 l, i = 1, 2 and 29.2.j, j = 1, 2) keep a constant value. A visual overview of the panels and the surrounding space is consistent with the appearance of the apparatus and implemented in accordance with methods known in the art.

 Depending on the purpose of the aircraft, the simulator can be attached to the drive system (22. 1 and 22.2), which is attached to the device to create overload (24) (Fig. 1 1, Fig. 12).

 The flight simulator, designed according to the method for the spatial design of flight simulators for aircraft and spacecraft, in particular, a table simulator with a single location in the cockpit, is intended for the training of pilot pilots. It is made for a Pilatus aircraft (RS-9M) and can be used for aircraft with a single location in the cockpit (Fig.9).

 The application of the method for the spatial design of simulators for aircraft and spacecraft for the Pilatus aircraft indicated, as an example above, is performed in the following sequence: in step 1. 1) from the initial stage with the necessary input data for the longitudinal movement:

one . one . 1) perform the calculations necessary to build balancing diagrams for the deviation of the elevator δ _Β ;

one . 1 .2) construct a balancing diagram for the deviation of the elevator δ „with respect to speed: δ _Β = f (V);

one . 1 .3) perform the calculations necessary to build balancing diagrams of the forces transmitted to the control handle when the steering wheel deviates the height P _in ;

one . 1 .4) to construct a balancing diagram for the forces transmitted to the control stick when the steering wheel deviates, the height Р „with respect to speed: Р _в = f (V);

one . 1 .5) draw up a balancing diagram for the forces transmitted to the control handle when the rudder is deflected P _in relation to the distance measured from the cab to move the control handle when the elevator deviates x _in : P _in = f (x _in ): one . fifteen. 1) draw a balance ovochnuyu diagram of the elevator deflection δ _Β with respect to the rate for the cruising speed In _cr eys. : δ _Β = f (V);

one . 1 .5.2) construct a balancing diagram according to the distance measured from the cabin while moving the control handle when the elevator wheel deviates from x _in relation to speed at x _in = δ _Β : x _in ⁼ f (V);

one . 1 .5.3) construct a balancing diagram for the forces transmitted to the control handle when the rudder is deflected by P _in relation to the speed V: P _в = f (V) and the distance measured from the cab to move the control handle when the elevator is deflected by x _in relative to the velocity V: _h = f (V) for the cruising speed from _Cray Y

From them, construct a balancing diagram for the forces transmitted to the control handle when the rudder is deviated from P _in relation to the distance measured from the cab for moving the control handle when the elevator is deviated from x _to : Р „= f (x _in ). From P "= f (x ') can be determined for a distance x" moves at applying the control knob _in the desired force F;

one . 1 .6) calculate the forces transferred to the control stick when the elevator is deflected when maneuvering with respect to speed and build balancing diagrams (dP _B / dn _y ) = f (V).

In the calculation and construction are taken from the maximum positive to the maximum negative overload p _y .

 When performing step 1 .2) from the initial stage with the necessary input data for lateral movement:

12. 1) perform the calculations necessary for the construction of balancing diagrams for the deviation of the rudder δ _Η :

 To build the balancing diagrams of the lateral movement is calculated:

 A) With a passing moment:

 1) steering angle;

 2) efforts transmitted to the pedals.

1 .2.2) construct a balancing diagram for the deviation of the rudder δ _Η with respect to the slip angle β: δ _Η = f (β);

1 .2.3) perform the calculations necessary to build a balancing diagram for the angle of heel γ; 1 .2.4) construct a balancing diagram for the deviation of the rudder δ _Η with respect to the angle of heel γ: δ _Η = f (γ);

 1 .2.5) perform calculations to construct a balancing diagram for the forces transmitted to the pedals Р „;

1 .2.6) construct a balancing diagram for the forces transmitted to the pedals P _n with respect to the angle of slip β: P _n = f (β);

1 .2.7) to construct a balancing diagram for the forces transmitted to the pedals P _n with respect to the angle of heel γ: P _n = f (γ).

 To build the balancing diagrams of the lateral movement are calculated:

 B) With a transverse moment:

 1) aileron deflection angle;

2) force transmitted to _^ control knob;

1 .2.8) perform the calculations necessary for constructing balancing diagrams for the deviation of aileron 6 _EL . ;

1 .2.9) to build a balancing diagram for the angle of deviation of ailerons 6 _EL . with respect to the slip angle β: 5 _EL . = f (β);

12. 1 0) to build a balancing diagram for the angle of deviation of the ailerons of 6 _E l with respect to the angle of heel y: 5 _EL = f (γ);

12. 1 1) to perform the calculations necessary to build balancing diagrams of the forces transmitted to the control stick when the ailerons R _el . ;

12. 1 2) to build a balancing diagram for the efforts ceasing to the control stick when the ailerons deviate R _el . in relation to the slip angle β: P _el. = f (β);

12. 1 3) to build a balancing diagram for the efforts transmitting to the control stick when the ailerons deviate R _el . in relation to the angle of heel γ: P _el . = f (γ).

 The sequence of the following steps is carried out according to the method for spatial design of simulators for aircraft and spacecraft. The final result of an exemplary performance on a Pilatus (RS-9M) aircraft, which is also applicable to aircraft with a single-seat pilots in the cockpit, is described by figures.

On Fig.3 presents a perspective view of this simulator. It consists of: five control blocks (7.m, m = 1... P, for n = 5) with monitors (2 1. m, m = l ... n, with n = 5) 3D LCD touch screen display is extremely thin. Monitors (21 .m, m = l ... n, for n = 5) are selected extremely thin to form the cabin, with a touch screen display - so that you can press the buttons with your hand, and 3 D visual visibility to give greater clarity in the cabin.

 Monitors (21. M, m = 1 ... n, with n = 5) with a size determined in accordance with the method for spatial design of simulators of size. The countertop (1) on which they are placed is designed according to JAR (Joint Aviation Requirements - General Aviation Requirements). It provides a constant minimum directional visual field of view 45 ° horizontally and 30 ° vertical field of view, as well as a constant oblique directionally directed from the pilot's cabin minimum directional visual field of view, provides 1 80 ° horizontally and 40 ° vertically field of view for each pilot. The table top (1) is held on the floor of the room on the supports (13). Supports (13) are fixed to it and the floor motionless.

 Pedals (2) are attached to the countertop (1). The aircraft control knob (3) is stationary.

 The seat (4) is movable and moves back so that the pilot can sit. Then move forward along axis (5) and lock with nut (30). The support (heaviness) (6) balances (balances) the structure and locks the seat (4) and nut (30) if they are pulled back.

 Figure 4 shows the simulator in the main view. A nut is placed in front of the weight (6), which is retained by the weight (6) and does not weaken when the seat is moved along the axis (5). In order to balance the design, in addition to the support (gravity) (6), the axis (5) is attached externally to the countertop (1).

 The control unit (7. 1), taken out forward, is connected with the test-testing device (9). The test-testing device (9) has a button that is pressed after the end of the flight to process information from the pilot data. It is connected to the printer after the added setting to associate it with the printer to display the processed information.

The support for the engine control knob (8) is attached to the countertop (1) and it is stationary. Pedals (2) are also attached to the countertop (1). Their regulation is carried out by a lift (regulator) (14), which moves them after the handle is pulled to adjust the cabin. On the countertop (1), the profile is formed (12), where the lift (regulator) (14) with pedals (2), which are fixed with a bar (10), are attached. The strap (10) is placed in a montage on the countertop (1), item X (1 1). The upper part of the lift (adjuster) (14) is movable 90 ° up and held by the ear (1 5. 1 and 15.2).

 Figure 5 shows the aircraft simulator top view. This allows you to see in detail the simulator inside. The control units (7.m, t = 2 ... 5) are brought out and one (7. 1) in front (to the right / left) by the pedals (2). The control unit (7.1), connected to the test-testing device (9), is moved left / right, their regulation can be performed by extended pedals (2). On the test-testing device (9), a display is shown on which the results of the flight are displayed.

 The place of the stand for the engine control knob (8), located in relation to the horizontal left monitor (21 .2), is shown. The aircraft control handle (3), through which the axis (5) passes, is fixed by means of the handle stopper, on the pedals (2) side and the nut (30) on the seat side (4) is fixed motionless to the floor of the room.

 From the inside, i.e. from the place where the seat (4) is pulled out and where the aircraft control handle (3) is set, the bearings are not placed outside. Only there the supports (1 3) are placed inside. This is provided so that the seat (4) and the pilot are pulled to the inside of the simulator.

 Figure 6 shows the aircraft simulator rear view. It shows more clearly the profile on the stand for the engine control knob (8). It is fixed to the countertop (1) and passes through the horizontal left monitor (21 .2). The joystick of the engine control knob is placed on the raised end part to the vertical left monitor (21 .4).

 To extend the pedals (2) back, there is a hole depending on the height (high) of the pilot (s) who will operate the aircraft.

Here on the simulator described, the seat (4) is locked with a nut (30). 7 shows the mechanism (30.0), with which the seat can also be locked. This mechanism consists of a flange (16) with a hole with a diameter equal to the diameter of this axis (5). Movable handles set aside (1 7. 1 and 1 7.2), which, after pulling the seat (4) forward, rotate 90 ° around the two axles. G ^{"n s mod al} profiles (1 8. 1 1 8.2), which are located on the closing bracket (1 9. 1 and 19.2) is also rotated by 90 ° and are closed. The opening between the two brackets has a diameter equal to the diameter of this axis etru (5). Their opening is made with a special key (20), shown in Fig. 8.

Application (use) of the invention

When applying the method to perform the simulator, the Pilatus flying machine (RS-9M), as well as on other devices in step 1 of step 1. 1) when performing the calculations necessary to build a balancing diagram for the elevator deflection, the following situation occurs, which is solved by the following method: when determining the elevator deflection angle δ _Β if the lateral moment coefficient at zero lifting force m _z o is unknown and not can be taken, the decision to adopt m _z o = 0, but then, to build a proper balancing charts sootvetstujushchie valid to take a cruising flight speed have _{to pe} fic. and build a real balancing diagram.

In step 1 of step 1. 1) when performing calculations necessary to construct balancing diagrams of force transmitted to the control knob at a deviation of the elevator P _in value may turn out to force P _to and hinge moment M _{w in} from maximum to minimum by increasing the number of Mach M corresponds to the minimum value. This is possible with an unknown value of the lateral moment coefficient at zero lifting force t ₂ о (since the angle of deviation of the elevator δ _Β from the number of Mach M increases, but with negative values, the force applied to the control handle when the elevator is deviated P _in decreases). To force exerted on the control handle when you reject elevator P _in at Mach number M used increased cruising speed have _{to p e} d a. and therefore the angle of deviation of the elevator δ _Β will also increase, i.e. with increasing deflection angle elevator δ _Β increases the force applied to the control handle when the elevator deviates P _in an increase in speed.

In step 1, from step 1 .2), in order to limit the amount of calculations when calculating the angle of attack, where the aerodynamic derivative of the lift coefficient s from the angle of attack C _y is taken in accordance with the Mach number M and the following is true: for example, for subsonic aircraft M = 0. 1 ... 0.9, a value is selected depending on the speed range a for the type of aircraft on which the simulator is made at subsonic flight speeds, such as M = 0.4.

 Using the method, simulators are created for various types of aircraft and spacecraft for a short period of time.

 The implementation of the simulator designed by this method makes it possible to perform flights as a visual view of the cockpit in the dimensions of both the aircraft and the surrounding space accessible for observation from the cockpit through monitors. Monitors are selected exclusively on thin ones to design the cab, with a touch screen display - so that you can press the buttons with your hand, and the 3 D visual overview gives greater clarity in the cab.

 This gives the pilot the opportunity to work out the same actions as when he is in the cockpit of the aircraft. The room in which the simulator is placed is selected according to its overall dimensions. The delivered support in one edge balances (balances) a design. The support for the engine / s control stick is placed and calculated according to the method for spatial design of simulators during the assembly of the simulator.

 The systems of visual overview of the surrounding area are also for real flight, including a map of the area, which provides information to the pilot for determining the location.

 Simulators of physical conditions, as a system for simulating special cases of flight, are represented by setting the sound signal from amplifiers that are either connected to the monitor or made to the monitor.

Flight data can be compared and even checked. With the help of the applied and calculated by the method of the test-testing device, an assessment is given for the correct technique of piloting the pilot. By comparing data from a real flight with that performed on The simulator displays the result (score). Data from the flight is also taken out graphically to be used in real flights.

 If more than one control unit is used, they all communicate with the cards and this allows them to work together.

 The invention makes it possible to train the flight crew on the correct action in real flight, such as takeoff, landing, flight in the airport area, etc. It also complies with the requirements adopted from the JAR (Joint Aviation Requirements - General Aviation Requirements) requirements for the complete formulation of the standards of the aviation trainer and meets the requirements of the motion system, visual and sound systems. The possible power of the equipment, its accuracy, resolution and dynamic response are sufficient to accurately reproduce the conditions of an aircraft simulator. The dynamics of efforts on the controls reproduces this as a simulated aircraft. The visual system meets all standards. A constant minimum directional visual field of observation of 45 ° horizontally and 30 ° vertically, and a constant oblique directionally directed from the pilot's cabin minimum directional visual field of observation is observed, provides a 180 ° horizontal 40 ° vertical field of observation for each pilot. It is a must for design countertops.

 An e and sound system is provided. Sound power control with amplifiers (invisible speakers) to a sound level that also meets the qualification requirements.

 In addition, for training purposes (such as take-off, landing, flying in the vicinity of the airport, training pilots' reactions, identifying control devices and practicing emergency situations), the simulator is also designed for maneuvering (to conduct military operations). For this purpose, it is attached to the drive system and device to create overload.

Using the proposed solution is made in accordance with the accepted requirements and allows you to both increase the flexibility of the simulator process and bring it to a large extent to a real (training) flight. It is also very economical in terms of its development and the means for its implementation. LITERATURE

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 6. Isov I. D. “Resistance on materialism”, Sofia, 1978.

Claims

The claims

one . A method for the spatial design of simulators for aircraft and spacecraft, consisting of the following stages: I initial stage, in which the following steps are performed:

 1) the calculation is semi-automated or automated by means of a computer and specialized software for deviations and forces transmitted to the sample / s to the handle / and control and construction of balancing diagrams for deviations and forces, using known physical dependencies for the corresponding apparatus for given input data, and additional (necessary in the calculation process) data, with an examination of the physical dependencies used, which are applied when managing the control units ION;

 2) the calculation is semi-automated or automated by means of a computer and specialized software of deviations and forces transmitted to the pedal sample / s and the construction of balancing diagrams of deviations and forces using known physical dependencies for the corresponding apparatus for given input data, and additional (necessary in the process of computing) data, with an examination of the used physical dependencies that are applied when managing the controls;

 3) comparison of results from t. 1 and t.2;

 4) making a simulator model with dimensions corresponding to the JAR requirements, corresponding to the type of apparatus for which the simulator is designed, in a suitable reduced scale, recreating the apparatus type cabin, selecting the scale and determining the dimensions (placement) of the simulator in an increasing scale, preserving the standard dimensions, measured cabins aircraft or spacecraft;

5) performing calculations for tension springs, using the control knobs / rods in the sample / s and pedals on the increasing scale, with the adoption of the permissible maximum size of the diameter D of the springs as a constant value; 6) a combination of the dimensions of the resulting layout, the real apparatus and monitors (three technological objects) and the design of the simulator's ideological project;

 II intermediate stage, in which the following actions are performed:

7) determination of the size of monitors and design of their actual sizes obtained using the formula:

R _n = MM / TS,

where R _n is the coefficient

 MM - monitor layout dimensions;

TS - dimensions of the panel of an aircraft or spacecraft

 xy = nx + Rny for n = 1, 2, 3, 4

Rxz ^~ Rnx + Rnz

where R _2y , R _xy , R _xz are the total coefficients in the fields Ozy, Okhu, Oxz R _nx , R _ny , R _nz are the coefficients equivalent to R _n with respect to the x, Y, z axis;

 n - number of monitors, relative to the location:

 1 - main monitor (s)

 2 - horizontal monitors

 3 - vertical monitors

 4 - monitor (s) located above the vertical and primary monitors

Rooiuo ⁼ (Rzy ⁺ Rxy ⁺ Rxz) / 3

where R ₀ 6iuo - coefficient for determining the size of monitors (for the choice of monitors)

 Rzy, Rxy, Rxz - total coefficients in the fields Ozy, Ohu, Oxz

Rczy ^~~ Rzy / 2; Rcxy ^- Rxy / 2, Rcxz ~ Rxz / 2

where R _CZ y, Rcxy, Rcxz are the coefficients for reducing the size of the simulator in the fields zy, xy, xz,

R _zy , R _xy , R _xz - total coefficients in the fields Ozy, Ohu, Oxz,

as values for R _n ; R _zy , R _xy , R _xz ; o6u>; R _czy , cxy, Rcxz are used to execute simulator drawings in 2D and 3D spaces, transfer project in space, determination of the maximum size of the simulator, determination of the size and number of monitors (selection of monitors) and its virtual assembly;

 8) preparation of 3D drawings in triplicate and drawing dimensions in three coordinate fields;

 9) selection of actual sizes, work with a software (drawing) product to obtain each individual part, and virtual assembly of the entire simulator design;

 10) drawing a real simulator on 2D working drawings, with the exception of the drawing of springs;

 III final stage, in which the following actions are performed:

 1 1) depending on the location of the springs operating on tension, in 3 D fields calculations are performed to determine their actual sizes, as:

 - calculation of maximum torque,

 - calculation of the maximum tensile springs,

 - verification of the maximum tangential stress at an established cross section of pure torsion,

 - calculation of the diameter of the cross section,

 - calculation of the number of active windings,

 - recording the result of the number of active windings,

 - choice of springs,

 - calculation of the minimum light opening,

 - calculation of the initial light hole,

 - calculation of the initial (free) length,

 - calculation of the length after the maximum and minimum load,

 - calculation of the lengths of the springs in tension,

 - calculation of the angle of inclination of the helix,

 - calculation of the step of the springs and recording the size of the springs,

 - calculation of the length of the helix,

 - calculation of the spring constant,

- the selection of the number of windings, in accordance with the distances obtained when designing the dimensions of the sample / s control knob and sample / s pedals, again calculating the maximum torque, maximum tensile springs, checking the maximum tangential stress at a fixed cross-section of pure torsion, calculating the diameter of the cross section,

 - calculation again of the maximum tension of the springs at the selected values of the number of active windings,

- determination of the coefficients k _xy , k _xz and k _{zy of the} springs in accordance with their location in the fields and performing additional calculations of the springs, as:

 - the choice of springs and the adoption of the minimum light aperture and previous calculations,

 - performing additional calculations of the initial light hole,

 - performing additional calculations of the initial (free) length,

- additional length calculations after the maximum load according to the formula:

L ₂ = L ₀ + max f + (k) * max f

 - performing additional length calculations after the minimum load,

 - performing additional calculations of the length of the springs in tension,

- performing additional calculations of the angle of inclination of the helix,

- performing additional calculations of the step of the springs,

 - description of the size of the springs,

 - performing additional calculations on the length of the helix,

- performing additional calculations of the spring constant by the formula:

 c = max P / (max f + (k) * max f),

while maintaining a constant value of the diameter D of the springs;

12) performing a comparison of the calculated sizes from t.1 1) of springs with maximum capabilities corresponding to the sizes that are determined by the actual sizes of the sample / handles of the handle / control wheels and the sample / pedals of the pedals, if the sizes obtained during the calculation do not correspond, return to t. 1 1), and if the dimensions obtained during the calculation correspond, therefore, the results obtained for the dimensions of the springs are put as final in the drawings for the sample / handles / ek controls and the sample / s of pedals and the remaining drawings are executed, which are not fulfilled in v.10).

2. The method, according to the claims 1, is characterized in that in t.1) the forces applied to the sample / control knobs / control are calculated in relation to speed, and in t.2) calculations for deviations and forces transmitted on the control stick.

3. The method, according to the claims 1 and 2, is characterized in that the calculations in 7) are entered in at least one table.

4. The method, according to the claims 1 to 3, is characterized in that the final stage can be performed before step 10) from the intermediate stage in cases where all other sizes are formed.

5. The flight simulator, according to the claims 1 to 4, consisting of at least one control unit (7.m, t - 1 ... p), a countertop (1), on which monitors are installed (21. m, t = 1 ... n) and which is supported by supports (13) inside and outside, as supports (13) are fixed to it and the floor motionless, with the exception of the side parts of the countertop (1), where the seat (4), supports (13) pass located only inside, the pedals (2) are regulated by a lift (regulator) (14), mounted in the profile (12) on the countertop (1), on which the product X (11) is mounted, in which it is delivered and the bar (10), locking the lift (regulator) (14) with pedals (2), the aircraft control handle (3), through which the axis (5) passes, which is fixed by the foot of the control handle (3) from the pedals (2) and which fixed motionless to the floor of the room, the seat (4) moving along the axis (5) and locked by a mechanism (30.0) or a nut (30), support (heaviness) (6) balancing structure, stand for the engine control handle (8), like a control handle aircraft (3) equipped with springs (29.1.i, i = 1,2), pedals (2) equipped with springs (29.2.j, j = 1,2) and a motor control handle the body represents the joysticks that are associated with the control unit (s) (7. Щ, m = l ... n), how to take the corresponding joystick and associated with the sample for the aircraft control handle (3), for the control handle engine - the joystick is mounted on a stand (8), pedals (2) with a lift (regulator) (14) are connected to the control unit / s (7.m, m = 1 ... p), loudspeaker, test-testing device (9), comparing the data of two flights, characterized in that the control stick sample and the pedal sample equipped with springs (29.1.1, i = 1,2 and 29.2.j, j = 1,2).

6. The flight simulator, according to claims 5, is characterized in that the springs (29.1 l, i = 1,2 and 29.2J, j = 1,2) are attached to the sample control sticks and the sample of pedals with the same diameter D.

7. The flight simulator, according to the claims 5 and 6, is characterized in that the seat (4) is equipped with straps (28) and a holder (26) for a circular surface (25), on which a table top (1) is attached through supports (13), to which a closed system of monitors is attached (21.m, m = l ... n), a drive system consisting of two rotating rings (22.1 and 22.2) located perpendicular to each other, mounted by struts (23.1 and 23.2) to the floor premises, a single automatic key (27) used to stop the drive system (22.1 and 22.2), a device for creating overload ki (24) which is connected to the control / they block / s (7.m, m = 1 ... n) and placed under a circular surface (25) on which the simulator is mounted.