RU2776669C1 - Wind tunnel of closed recirculation type - Google Patents

Abstract

FIELD: sports equipment.

SUBSTANCE: invention relates to a device for simulating sports exercises in an air stream, namely to wind tunnels of a closed recirculation type, which can be used for aerodynamic studies of the technique of performing exercises by a person (athlete, pilot) in various professional disciplines, including for sports testing and testing professional equipment for athletes, pilots, parachutists. In the preferred embodiment, the wind tunnel of the closed recirculation type contains a fan assembly, a confuser, a flight chamber, a diffuser, a return air duct and a set of rotary air ducts that combine the elements of the wind tunnel into a single system. In this case, the flight chamber is made with at least one curved section, which is made with the profile of the curved trajectory covered by a section of the Cornu spiral.

EFFECT: most complete and accurate simulation of the airflow in relation to the specific flight configuration of the athlete pilot.

16 cl, 6 dwg, 2 tbl

Description

FIELD OF TECHNOLOGY TO WHICH THE INVENTION RELATES

The invention relates to a device for simulating sports exercises in an air stream, namely to wind tunnels of a closed recirculation type, which can be used for aerodynamic studies of the technique of performing exercises by a person (athlete, pilot) in various professional disciplines, including for sports testing and conducting testing professional equipment for athletes, pilots, parachutists.

BACKGROUND OF THE INVENTION

Wind tunnels of the proposed type should form an air flow with the characteristics necessary to perform simulation exercises in the closest to natural real conditions.

Therefore, the most important factor when choosing a wind tunnel design is the ability to most accurately simulate the air flow for aerodynamic studies, including such basic characteristics as the required air flow speed, its uniformity - the absence of turbulence, and the creation of the necessary real angles of attack of the air flow in relation to the pilot's flight configuration. athlete.

From the international publication WO2017/142461, a wind tunnel for free human soaring in the air with an adjustable airflow angle in the working chamber is known, containing a tunnel consisting of two working sections with a flexible connecting part that allows you to adjust the above-mentioned airflow angles in the working chamber, the first section has a preferred angle of 15 - 60°, and the second section in the range of 5 - 85°, while the angles can be adjusted using an actuator in the form of a hydraulic cylinder, and the heterogeneity of the air flow in the sections can be corrected using small holes in the walls of the tunnel, through which the outside air, getting into problem areas, leads to a decrease in the uneven separation of the flow from the wall of the formed vortex.

A disadvantage of the known wind tunnel is the complexity of the design due to the use of flexible joints of the air ducts, which can lead to significant hydraulic losses in the joints when the angle of their installation relative to the horizontal axis is changed both in the air flow and due to partial leakage of the joints.

Since the coefficient of hydraulic losses depends on the angle of rotation of the flow, i.e. with a larger angle of rotation, correspondingly, large hydraulic losses occur, therefore, the presence of sharp drops in the joints on the rotary knees of a well-known wind tunnel can generally lead to unacceptable hydraulic losses, turbulence and uneven flow in the working area and, accordingly, to increased power consumption of the fan installation.

Another analogue, the closest in its technical essence to the proposed invention, is the design of the device "Simulator of parachute jumps in a wind tunnel", described in the international publication WO2018/015766, containing a flight chamber with a section inclined and curved to the vertical plane, the shape of this curve has smooth transition from approximately horizontal to approximately vertical where the first part of the flight chamber can be set from 0 to 45° horizontal and the last part of the flight chamber from 45 to 90° horizontal, or the curved surface is curved in two or more dimensions, or curvature curved surface is defined by a spline.

The disadvantages of the known device is the uncertainty of the formation of the air flow in the flight chamber. Moreover, for each specific sports discipline, for example, WingSuit jumping or ski jumping, its own flight path is required, due to the presence of specific angles of attack of the athlete's configuration in relation to the moving air flow in the working area of the wind tunnel.

DISCLOSURE OF THE INVENTION

The present invention aims to overcome the above disadvantages of the prior art and solves the technical problem of providing the most complete and accurate airflow simulation for a particular athlete pilot flight configuration.

In one aspect of the invention, a closed recirculation type wind tunnel is provided, comprising:

a fan assembly, a confuser, a flight chamber, a diffuser, a return air duct and a plurality of rotary air ducts that combine elements of the wind tunnel into a single system, while

the flight chamber is made with at least one curved section, which is made with a curved trajectory profile described by a section of the Cornu spiral.

The present invention provides the most complete simulation of the various modes of flight configurations of athletes who use in their performances the free hover of a person in the air, such as skydivers, as well as gliding, gliding along the air stream, such as WingSuit or ski jumpers, so that a similar profile of the curve ensured the uniformity of the air flow in its cross section and their stable sliding in the airspace in all three-dimensional planes both along the positive and negative directions of movement of the coordinate axes, as well as stable sliding at a positive or negative angle of attack of the pilot configuration relative to the moving air flow.

The technical result is achieved due to the fact that in a wind tunnel for simulating human exercises in an air flow containing a flight chamber with at least one curved section, which is made with a curved trajectory profile described by a section of the Cornu spiral (which is also known as a clothoid or Euler spiral , i.e. a curve whose curvature varies linearly as a function of arc length). This ensures the continuity of the curvature function with the minimum possible rate of curvature change for a given length and, accordingly, with the minimum rate of rise of the centrifugal force at a constant speed along the generatrix of the air flow curve. The minimum increase in centrifugal force determines the uniformity of the air flow in the curvilinear flight chamber and the reduction of hydraulic losses.

In a further embodiment, a wind tunnel is provided in which at least one curved section of the flight chamber is configured with a curved trajectory profile described by a section of the negative branch of the Cornu spiral.

In a further embodiment, a wind tunnel is provided in which at least one curved portion of the flight chamber is configured with a curved trajectory profile described by a portion of the positive branch of the Cornu spiral.

In an additional embodiment, a wind tunnel is proposed in which the flight chamber is made with two curved sections, the first curved section is made with a curved trajectory profile described by a section of the negative branch of the Cornu spiral, and the second curved section is made with a curved trajectory profile described by a section of the positive branch of the spiral Cornu.

In a further embodiment, a wind tunnel is provided in which:

an entry-exit node is provided in the upper part of at least one curved section of the flight chamber, and/or

an entry-exit unit is provided in the lower part of at least one curved section of the flight chamber.

In an additional embodiment, a wind tunnel is proposed in which the flight chamber is made with two curved sections, and the entry-exit node located in the upper part of the first curved section and the entry-exit node of the second curved section are a single node.

In a further embodiment, a wind tunnel is provided that includes a vertical portion of the flight chamber.

In a further embodiment, a wind tunnel is provided that provides an inlet/outlet assembly at the bottom of a vertical portion of the flight chamber.

In a further embodiment, a wind tunnel is provided in which the vertical portion of the flight chamber is located above at least one of the curved portions of the flight chamber.

In a further embodiment, a wind tunnel is provided in which a safety net is provided below the vertical portion of the flight chamber but above at least one of the curved portions of the flight chamber.

In an additional embodiment, a wind tunnel is proposed in which the vertical section of the flight chamber is located above the curved section of the flight chamber, made with a curved trajectory profile described by a section of the positive branch of the Cornu spiral, while in the upper part of the curved section of the flight chamber, an entry-exit node is provided for access and into the curved portion of the flight chamber and into the vertical portion of the flight chamber.

In a further embodiment, a wind tunnel is provided in which a vertical portion of the flight chamber is located below at least one of the curved portions of the flight chamber.

In a further embodiment, a wind tunnel is provided in which a safety net is provided above the vertical portion of the flight chamber but below at least one of the curved portions of the flight chamber.

In an additional embodiment, a wind tunnel is provided in which a safety net is provided below the flight chamber, preferably such a safety net is located between the confuser and the flight chamber.

In an additional embodiment, a wind tunnel is proposed, in which a monorail is mounted along the profile of the curved trajectory of at least one curved section, along which a suspension cart moves, made with the possibility of holding an athlete.

In a further embodiment, a wind tunnel is provided that provides an inlet/outlet assembly at the top of the diffuser.

It should be understood that in additional embodiments of the invention the above technical result is also provided.

In the following description, embodiments of the proposed invention, as well as the positive effects of its implementation, are shown and described in more detail.

BRIEF DESCRIPTION OF THE DRAWINGS

The invention is illustrated in the figures of the drawings, in which:

Figure 1 shows the Cornu spiral, the sections of which describe the trajectory of the profile of the curved section of the flight chamber.

Figure 2 shows an embodiment of a wind tunnel according to the present invention, containing a curved section of the flight chamber with a curved trajectory profile described by a section of the negative branch of the Cornu spiral.

Figure 3 shows an embodiment of the wind tunnel according to the present invention, containing a curved section of the flight chamber with a curved trajectory profile described by a section of the positive branch of the Cornu spiral.

Figure 4 shows another embodiment of the wind tunnel according to the present invention, containing a curved section of the flight chamber with a curved trajectory profile described by a section of the positive branch of the Cornu spiral.

Figure 5 shows another embodiment of the wind tunnel according to the present invention, containing a curved section of the flight chamber with a curved trajectory profile described by a section of the negative branch of the Cornu spiral.

Figure 6 shows another embodiment of the wind tunnel according to the present invention, containing two curved sections, one of which is made with a curved trajectory profile described by a section of the negative branch of the Cornu spiral, and the other is made with a curved trajectory profile described by a section of the positive branch of the Cornu spiral .

DESCRIPTION OF THE PREFERRED EMBODIMENTS

The present invention relates to a device for simulating sports exercises in an air flow, namely to wind tunnels of a closed recirculation type, which can be used for aerodynamic studies of the technique of performing exercises by a person (athlete, pilot) in various professional disciplines, including sports testing and testing of professional equipment for athletes, pilots, paratroopers.

With reference to the accompanying drawings, in one aspect of the present invention, a closed recirculation type wind tunnel is provided, comprising:

fan assembly 1, confuser 4, flight chamber 5, diffuser 10, return air duct 19 and a plurality of rotary air ducts 2, which combine elements of the wind tunnel into a single system, while

the flight chamber 5 is made with at least one curved section 7, 8, which is made with a profile 6 of a curved trajectory described by a section of the Cornu spiral.

It should be understood that, although individual components and elements of the proposed wind tunnel are not shown in the figures, they are provided by the present invention and can be made by known means and methods. For example, cooling devices installed in the return air duct, noise-absorbing elements in rotary air ducts, safety elements in the flight chamber or anti-vibration supports for installing a wind tunnel, which are essentially disclosed in the Russian Federation patent for invention No. 2693106 and/or Russian patent for invention No. 2692744, the materials of which are fully incorporated into the materials of the present invention by reference.

In FIG. 1 shows the Cornu spiral, which is described by the following system of equations.

In this case, the curve determined for s < 0 is considered to be the negative (or left, or lower) branch of the Cornu spiral, and the curve determined for s > 0 is considered to be the positive (or right, or upper) branch of the Cornu spiral.

, откуда следует, что если нужен угол θ=90°, то u = ± 1 и т.д. Эти значения не зависят от параметров a и b, то есть от размеров кривой слева и справа. Для фиг. 1 значения параметров a и b равны.In FIG. 1 shows the value of the parameter u at different points of the curve. Let θ be the angle made by the tangent to the Cornu spiral at a given point to the x-axis, then θ

, whence it follows that if the angle θ=90° is needed, then u = ± 1, etc. These values do not depend on the parameters a and b , that is, on the dimensions of the curve on the left and right. For FIG. 1 the values of parameters a and b are equal.

The place of trimming the spiral can be chosen depending on the required angle of inclination of the tangent to the abscissa axis. In this case, the curve can be cut off anywhere, limiting the area of change of the parameter s . Thus, the scaling of an inclined curvilinear air duct formed by the Cornu spiral can be performed in any arbitrary parameters, while the uniformity of the air flow is maintained in any cross section of the air duct.

As a non-limiting example, below is the calculation of the curved section 7 of the flight chamber, which is made with a curved trajectory profile described by a section of the negative branch of the Cornu spiral.

Assume that the flight chamber curved portion 7 is to extend from a substantially horizontal portion (θ=0°) to a substantially vertical portion (θ=90°) as viewed in the direction of flight. Accordingly, u is chosen from 0 to -1. It should be understood that for the direction of the air flow, such a section, on the contrary, will extend from a substantially vertical section (θ=90°) to a substantially horizontal section (θ=0°). The coordinates of the x and y parameters are given in Table 1 below for different values of the b parameter.

Tab. one

b =1 b =5 b =9 u x y x y x y 0 0 0 0 0 0 0 -0.1 -0.099998 -0.0005236 -0.49999 -0.00262 -0.89998 -0.00471 -0.2 -0.199921 -0.0041876 -0.99961 -0.02094 -1.79929 -0.03769 -0.3 -0.299401 -0.014117 -1.49701 -0.07059 -2.69461 -0.12705 -0.4 -0.397481 -0.0333594 -1.98741 -0.1668 -3.57733 -0.30023 -0.5 -0.492344 -0.0647324 -2.46172 -0.32366 -4.4311 -0.58259 -0.6 -0.581095 -0.11054 -2.90548 -0.5527 -5.22986 -0.99486 -0.7 -0.659652 -0.172136 -3.29826 -0.86068 -5.93687 -1.54922 -0.8 -0.722844 -0.249341 -3.61422 -1.24671 -6.5056 -2.24407 -0.9 -0.764823 -0.339776 -3.82412 -1.69888 -6.88341 -3.05798 -one -0.779893 -0.438259 -3.89947 -2.1913 -7.01904 -3.94433

Thus, the overall dimensions of the calculated curved section 7 of the flight chamber in the most preferred variant, at b = 9, are about 4 m in height and about 7 m in width. Accordingly, to reduce the overall dimensions, the parameter b should be reduced. Conversely, to increase the overall dimensions, the b parameter should be increased.

As another non-limiting example, below is the calculation of the curved section 8 of the flight chamber, which is made with a curved trajectory profile described by a section of the positive branch of the Cornu spiral.

Assume that the flight chamber curved portion 8 is to extend from a substantially vertical portion (θ=90°) to a substantially horizontal portion (θ=0°) as viewed in the direction of flight. Accordingly, u is chosen from 1 to 0. It should be understood that for the direction of air flow, such a section, on the contrary, will extend from an essentially horizontal section (θ=0°) to an essentially essentially vertical section (θ=90°). The coordinates of the x and y parameters are given in Table 2 below for different values of the a parameter.

Tab. 2

a=1 a=5 a=9 u x y x y x y 0 0 0 0 0 0 0 0.1 0.099998 0.0005236 0.499988 0.002618 0.899978 0.004712 0.2 0.199921 0.0041876 0.999605 0.020938 1.799289 0.037688 0.3 0.299401 0.014117 1.497005 0.070585 2.694609 0.127053 0.4 0.397481 0.0333594 1.987405 0.166797 3.577329 0.300235 0.5 0.492344 0.0647324 2.46172 0.323662 4.431096 0.582592 0.6 0.581095 0.11054 2.905475 0.5527 5.229855 0.99486 0.7 0.659652 0.172136 3.29826 0.86068 5.936868 1.549224 0.8 0.722844 0.249341 3.61422 1.246705 6.505596 2.244069 0.9 0.764823 0.339776 3.824115 1.69888 6.883407 3.057984 one 0.779893 0.438259 3.899465 2.191295 7.019037 3.944331

Thus, the overall dimensions of the calculated curvilinear section 8 of the flight chamber in the most preferred variant, with a = 9, are about 4 m in height and about 7 m in width. Accordingly, to reduce the overall dimensions, the parameter a should be reduced. And vice versa, to increase the overall dimensions, the parameter a should be increased.

As shown in FIG. 2 and 5, in a preferred embodiment, a wind tunnel is proposed in which at least one curved section 7 of the flight chamber is provided with a curved trajectory profile described by a section of the negative branch of the Cornu spiral. This embodiment of the wind tunnel is preferred for training ski jumpers.

As shown in FIG. 3 and 4, in a preferred embodiment, a wind tunnel is proposed in which at least one curved section 8 of the flight chamber is provided with a curved trajectory profile described by a section of the positive branch of the Cornu spiral. This wind tunnel embodiment is preferred for training WingSuit jumpers.

Finally, as shown in FIG. 6, in the preferred embodiment, a wind tunnel is proposed, in which the flight chamber is made with two curved sections, the first curved section 7 is made with a curved trajectory profile described by a section of the negative branch of the Cornu spiral, and the second curved section 8 is made with a curved trajectory profile described by a section positive branch of the Cornu spiral. Accordingly, this wind tunnel embodiment is preferred for training both ski jumpers and WingSuit jumpers.

It is to be understood that substantially the same elements are designated by the same reference numerals throughout the various figures. Thus, for example, the rotary air ducts 2 may be elements that provide a change in the air flow inside the wind tunnel by 90°, 180°, 270° or any other angle necessary to provide a single air flow path inside the wind tunnel. All such rotary ducts will be identified by reference numeral 2.

In addition, it should be understood that some components and elements of the wind tunnel may not be shown in some figures for simplification. However, this does not mean that they are not present in the embodiment illustrated in this figure. For example, in FIG. 2-3 do not show the confuser, honeycomb, and diffuser, but they may be provided in the wind tunnel configuration of FIG. 2-3, unless otherwise expressly stated in the description materials. In addition, the duct 91 is not essentially a return duct 19 for directing air flow from the flight chamber 5 to the fan assembly 1, but a duct through which the air flow is directed from the fan assembly 1 to the curved flight chamber. However, their design is essentially the same and is generally a cylindrical tube or a tube with a rectangular cross section.

Continuing generally with FIG. 2-6, the operation of the proposed wind tunnel will be described. When the fan unit 1 is turned on, containing one or more fans located in the air duct, a pressure difference is created, under the influence of which the air flow from the fan through the rotary elbow 2 enters the honeycomb 3. In the honeycomb 3, the field of air flow velocities is equalized. Further, in the confuser 4, as a result of a smooth narrowing of the passage section, the air flow is accelerated to a specific flight configuration that provides the necessary stable support for the pilot in the air flow of the flight chamber.

In one of the embodiments, a wind tunnel is proposed, in which a safety net 18 is provided below the flight chamber, preferably, such a safety net is located directly between the confuser 4 and the lower section of the flight chamber. This safety net 18 also helps to equalize the field of air flow velocities.

The airflow rate inside the flight chamber can be controlled automatically or at the operator's command using a control system (not shown) containing frequency converters for adjustable electric motors (not shown) of the fan assembly.

The air flow, having passed through the flight chamber 5, enters the rotary air duct 2, the return air duct 19 and then to the inlet of the axial discharge fan assembly 1.

The movement of the air flow in the flight chamber occurs along a curvilinear trajectory, the profile 6 of which is formed by the Cornu spiral. In this case, as mentioned above, the generatrix of the left lower branch in negative coordinates (-x; -y) forms the section 7 of the flight chamber, which can be used, for example, for imitation exercises of ski jumpers. The generatrix of the right upper branch in positive coordinates (+x;+y) forms section 8 of the flight chamber, which in turn is used, for example, for simulation exercises of WingSuit jumpers.

To fly in a curved wind tunnel, an athlete or a pilot can enter the flight chamber through several openings that can be provided in the proposed wind tunnel. These door openings or entry-exit nodes can also be used to exit the flight chamber. Such entry-exit nodes can be made similar to the revolving doors, which are essentially disclosed in the RF patent for the invention No. 2693106 and/or the RF patent for the invention No. 2692744, which were mentioned above.

In one of the embodiments, a wind tunnel is proposed, in which an entry-exit assembly 13, 15 is provided in the upper part of at least one curved section of the flight chamber, and/or an entry-exit assembly 15, 17 is provided in the lower part of at least one curved flight chamber area.

It should be understood that, depending on the configuration of the wind tunnel, various numbers, combinations, and locations for accommodating entry-exit nodes are possible.

For example, in one embodiment, a wind tunnel is provided in which the flight chamber is provided with two curved portions 7, 8 as shown in FIG. 6, wherein the entry/exit assembly 15 located at the top of the first curved portion 7 and the entry/exit assembly 15 of the second curved portion 8 are essentially a single assembly.

Thus, the following access to the flight chamber of the proposed wind tunnel is provided: the entry-exit assembly 13 is used to enter the flight chamber on a curvilinear section 8 of positive curvature, i.e. on a section that is made with a profile of a curvilinear trajectory described by a section of the positive branch of the Cornu spiral, for performing exercises by WingSuit jumpers.

The input-output node 15 is used to exit the flight chamber at the curved section 8 of positive curvature and to enter the flight chamber at the curved section 7 of negative curvature, i. e. on a section that is made with a profile of a curvilinear trajectory described by a section of the negative branch of the Cornu spiral, where exercises by ski jumpers and horizontal flight exercises at low angles of attack can be performed.

The entry-exit node 17 is used to exit the flight chamber in a curved section 7 of negative curvature, where exercises by ski jumpers and horizontal flight exercises at high angles of attack can be performed.

Accordingly, it is possible to carry out a combined flight. To do this, the athlete uses the entry-exit node 13 to enter the flight chamber on the curved section 8 of positive curvature, makes a jump (flight) along two curved sections 7, 8 and uses the entry-exit node 17 to exit the flight chamber on the curved section 7 of negative curvature.

Depending on the priority of training, such as ski jumping, and the required flight configuration in simulating sports exercises, the inclined curved wind tunnel can be made with a flight chamber containing only a curved section 7 of negative curvature, as shown in FIG. 2. During a real jump and exit of the skier 20 from the take-off table, the direction of the air flow 21 in relation to the jumping skier 20 can be an angle of attack 22 of about 10°, and during the further flight until landing, the angle of attack 23 can increase up to 40°.

Alternatively, an inclined curved wind tunnel may be provided with a flight chamber containing only a curved portion 8 of positive curvature, as shown in FIG. Such a wind tunnel may be primarily intended for training WingSuit athletes. When jumping, the angle of attack 24 at the beginning of the flight of the pilot 25 can take both positive and negative values, and at the end of the flight when braking to open the parachute, the angle of attack 26 can take on significant positive values.

Moreover, in additional embodiments, a wind tunnel can be provided, in which a vertical section 11 of the flight chamber is also provided. The vertical section 11 of the flight chamber is used to perform free-floating exercises for skydivers. In this case, the wind tunnel may be provided with an input-output node 12 in the lower part of the vertical section 11 of the flight chamber.

In additional embodiments, see, for example, FIG. 4 and 6, a wind tunnel is provided in which the vertical section 11 of the flight chamber is located above at least one of the curved sections 7, 8 of the flight chamber. Preferably, the vertical section 11 is located above the curvilinear section 8 of positive curvature, as in this case, it is not necessary to use additional rotary ducts to redirect the air flow.

In additional embodiments, a wind tunnel is provided in which a safety net 18 is provided below the vertical section 11 of the flight chamber, but above at least one of the curved sections 7, 8 of the flight chamber. place of installation. The safety net 18 can be used when less experienced athletes are training on the vertical section 11 of the flight chamber. On the contrary, if more experienced athletes train in a wind tunnel, then the safety net can be removed, while providing the possibility of performing combined training both with soaring in the vertical section 11 of the flight chamber, and with flying in the curved sections located below.

Thus, in one of the most preferred options, a wind tunnel is proposed, in which the vertical section 11 of the flight chamber is located above the curved section 8 of the flight chamber, made with a profile of a curved trajectory described by a section of the positive branch of the Cornu spiral, while in the upper part of the curved section 8 The flight chamber is provided with an entry-exit node 12 for access to both the curved section 8 of the flight chamber and the vertical section 11 of the flight chamber (see, for example, Fig. 4).

In addition, a wind tunnel can be provided in which the vertical section 11 of the flight chamber is located below at least one of the curved sections 7, 8 of the flight chamber. Preferably, the vertical section 11 of the flight chamber is located below the curved section 7 of negative curvature, because in this case, it is not necessary to use additional rotary ducts to redirect the air flow.

Additionally, above the vertical section 11 of the flight chamber, but below at least one of the curved sections 7, 8 of the flight chamber, a safety net 18 is provided, which increases the safety of jumping and flying in the curved sections 7, 8 located above the flight chamber. It should be understood that such a safety net 18 may be retractable to enable combined jumping and flying.

In addition, in some embodiments of the implementation of the wind tunnel, an input-output node 9 can be provided in the upper part of the diffuser 10, in which case it is possible to perform base jumping exercises for skydivers.

Accordingly, with the wind tunnel configuration shown in FIG. 6, in the absence of a safety net 18, which can be provided below the vertical section 11 of the flight chamber, it is possible to make a complex jump, in which the athlete enters through the entry-exit node 9 into the upper part of the diffuser 10, jumps off a cliff (base jumping), hovers in a vertical section 11 of the flight chamber and goes into a complex flight at different angles of attack, moving along the curved sections 7 and 8 of the flight chamber. Completing the jump at the bottom of the flight chamber, the athlete leaves it through the entry-exit node 17. If necessary, the jump (flight) can be interrupted and the athlete can leave the flight chamber through one of the other provided entry-exit nodes 12, 13, 15.

In yet another additional embodiment of the invention, a wind tunnel is proposed, in which a monorail 29 is mounted along the profile 6 of the curved trajectory of at least one curved section 7, 8, along which the suspended cart 28 moves, made with the possibility of holding the athlete. To securely hold the athlete, a cable suspension 27 can be used, which is attached at one end to the suspension cart 28, and holds the athlete at the other end. Thus, the safety of the movement of the athlete 20 and 25 along the generatrix of the air flow 21 of the inclined curved wind tunnel is additionally ensured.

In each of the embodiments described above, the technical result is provided due to the fact that in the wind tunnel for simulating human exercises in the air flow, a flight chamber is provided with at least one curvilinear section, which is made with a curved trajectory profile described by a section of the Cornu spiral. This ensures the continuity of the curvature function with the minimum possible rate of curvature change for a given length and, accordingly, with the minimum rate of rise of the centrifugal force at a constant speed along the generatrix of the air flow curve. The minimum increase in centrifugal force determines the uniformity of the air flow in the curvilinear flight chamber and the reduction of hydraulic losses.

Thus, the present invention guarantees the most complete imitation of various modes of flight configurations of athletes who use in their performances the free hover of a person in the air, such as skydivers, as well as gliding, gliding along the air stream, such as WingSuit or ski jumpers, such in such a way that such a profile of the curve ensures the uniformity of the flow of the air flow in its cross section and their stable sliding in the air space in all three-dimensional planes both along the positive and negative directions of movement of the coordinate axes, as well as stable sliding at a positive or negative angle of attack of the configuration pilot relative to the moving air stream.

While exemplary embodiments have been described in detail and shown in the accompanying drawings, it should be understood that such embodiments are illustrative only and are not intended to limit the wider invention, and that the present invention should not be limited to the particular arrangements and structures shown and described. as various other modifications may be apparent to those skilled in the art.

One of ordinary skill in the art will appreciate that the embodiments covered by the present description are not limited to the specific illustrative embodiments described above. In this regard, although illustrative embodiments have been shown and described, a wide range of modifications, changes, combinations, and substitutions is contemplated in the foregoing description. It should be understood that in the foregoing, such variations can be made without departing from the scope of the present invention. Accordingly, it is advisable to interpret the appended claims broadly and in a manner consistent with the present disclosure.

LIST OF REFERENCES

1 - Fan assembly

2 - Rotary air duct

3 - Honeycomb

4 - Confuser

5 - Flight camera

6 - Curvilinear trajectory profile of the flight chamber

7 - Curvilinear section of the flight chamber with negative curvature

8 - Curvilinear section of the flight chamber with positive curvature

9 - Diffuser entry-exit unit

10 - Diffuser

11 - Vertical section of the flight chamber

12 - Node entry-exit to the vertical section

13 - Node of entry-exit to the curvilinear section of positive curvature

15 - Node of entry-exit to curvilinear sections of negative curvature and positive curvature

17 - Node of entry-exit to the curvilinear section of negative curvature

18 - Safety net

19 - Return duct

20 - Ski jumper

21 - Direction of air flow in the flight chamber

22, 23 - Angles of attack between airflow direction and ski jumper configuration

24, 26 - Angles of attack between airflow direction and WingSuit pilot configuration

25 – WingSuit Pilot

27 - Cable suspension

28 – Monorail trolley

29 – Monorail

91 - Duct

Claims (20)

1. Wind tunnel closed recirculation type, containing: fan assembly (1), confuser (4), flight chamber (5), diffuser (10), return air duct (19) and a plurality of rotary air ducts (2) that combine elements of the wind tunnel into a single system, while the flight chamber (5) is made with at least one curved section (7, 8), which is made with a profile (6) of a curved trajectory described by a section of the Cornu spiral. 2. The wind tunnel according to claim 1, in which at least one curvilinear section (7) of the flight chamber is made with a curved trajectory profile described by a section of the negative branch of the Cornu spiral. 3. Wind tunnel according to claim 1, in which at least one curvilinear section (8) of the flight chamber is made with a curved trajectory profile described by a section of the positive branch of the Cornu spiral. 4. The wind tunnel according to claim 1, in which the flight chamber is made with two curved sections, the first curved section (7) is made with a curved trajectory profile described by a section of the negative branch of the Cornu spiral, and the second curved section (8) is made with a curved profile trajectory described by a section of the positive branch of the Cornu spiral. 5. Wind tunnel according to any one of paragraphs. 1-4, in which: an inlet-outlet assembly (13, 15) is provided in the upper part of at least one curved section of the flight chamber, and/or an input-output unit (15, 17) is provided in the lower part of at least one curved section of the flight chamber. 6. The wind tunnel according to claim 5, in which the flight chamber is made with two curved sections (7, 8), and the input-output node (15) located in the upper part of the first curved section (7), and the input node (15) - exits of the second curved section (8) are a single unit. 7. Wind tunnel according to any one of paragraphs. 1-4, in which a vertical section (11) of the flight chamber is provided. 8. A wind tunnel according to claim 7, in which an inlet-outlet assembly (12) is provided in the lower part of the vertical section (11) of the flight chamber. 9. Wind tunnel according to claim 7, in which the vertical section (11) of the flight chamber is located above at least one of the curved sections (7, 8) of the flight chamber. 10. The wind tunnel according to claim 9, in which a safety net (18) is provided below the vertical section (11) of the flight chamber, but above at least one of the curved sections (7, 8) of the flight chamber. 11. The wind tunnel according to claim 8, in which the vertical section (11) of the flight chamber is located above the curved section (8) of the flight chamber, made with a profile of a curved trajectory described by a section of the positive branch of the Cornu spiral, while in the upper part of the curved section (8 ) of the flight chamber, an entry-exit unit (12) is provided for access to both the curved section (8) of the flight chamber and the vertical section (11) of the flight chamber. 12. The wind tunnel according to claim 7, in which the vertical section (11) of the flight chamber is located below at least one of the curved sections (7, 8) of the flight chamber. 13. The wind tunnel according to claim 12, in which a safety net (18) is provided above the vertical section (11) of the flight chamber, but below at least one of the curved sections (7, 8) of the flight chamber. 14. Wind tunnel according to any one of paragraphs. 1-13, in which a safety net (18) is provided below the flight chamber, preferably such a safety net is located between the confuser (4) and the flight chamber. 15. Wind tunnel according to any one of paragraphs. 1-14, in which along the profile (6) of the curved trajectory of at least one curved section (7, 8) a monorail (29) is mounted, along which a suspension cart (28) moves, made with the possibility of holding the athlete. 16. Wind tunnel according to any one of paragraphs. 1-15, in which an inlet-outlet assembly (9) is provided in the upper part of the diffuser (10).

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