WO2017006251A1 - Soufflerie à flux de recirculation, en particulier pour simulations de chute libre ou de parachutage - Google Patents

Soufflerie à flux de recirculation, en particulier pour simulations de chute libre ou de parachutage Download PDF

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Publication number
WO2017006251A1
WO2017006251A1 PCT/IB2016/054036 IB2016054036W WO2017006251A1 WO 2017006251 A1 WO2017006251 A1 WO 2017006251A1 IB 2016054036 W IB2016054036 W IB 2016054036W WO 2017006251 A1 WO2017006251 A1 WO 2017006251A1
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WO
WIPO (PCT)
Prior art keywords
duct
wind tunnel
substantially vertical
air flow
truncated cone
Prior art date
Application number
PCT/IB2016/054036
Other languages
English (en)
Inventor
Gianni MENGA
Carlos EURIBE
Original Assignee
Extreme Flight Fze
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Extreme Flight Fze filed Critical Extreme Flight Fze
Publication of WO2017006251A1 publication Critical patent/WO2017006251A1/fr

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Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
    • G01M9/02—Wind tunnels
    • A—HUMAN NECESSITIES
    • A63—SPORTS; GAMES; AMUSEMENTS
    • A63G—MERRY-GO-ROUNDS; SWINGS; ROCKING-HORSES; CHUTES; SWITCHBACKS; SIMILAR DEVICES FOR PUBLIC AMUSEMENT
    • A63G31/00—Amusement arrangements
    • A—HUMAN NECESSITIES
    • A63—SPORTS; GAMES; AMUSEMENTS
    • A63G—MERRY-GO-ROUNDS; SWINGS; ROCKING-HORSES; CHUTES; SWITCHBACKS; SIMILAR DEVICES FOR PUBLIC AMUSEMENT
    • A63G31/00—Amusement arrangements
    • A63G2031/005—Skydiving

Definitions

  • TITLE "Recirculat ing-flow wind tunnel, in particular for free-falling or parachuting simulations"
  • the present invention relates to a recirculat ing-flow wind tunnel, in particular for free-falling or parachuting simulations .
  • Wind tunnels are known in the art, in particular wind tunnels for free-falling or parachuting simulations. Wind tunnels, which generally have a closed-circuit design, suffer from a few drawbacks.
  • Another drawback is that they have a structure that can generate a tortuous, or anyway energy-consuming, air flow .
  • one of the technical problems that are solved by the present invention is how to create a wind tunnel having a simple structure and a flight chamber with an advantageous conformation.
  • Another object of the invention is to create an energetically efficient wind tunnel.
  • FIG. 1 is a front view of a wind tunnel in accordance with a preferred embodiment of the present invention.
  • Figure 1 schematically shows a wind tunnel in accordance with a preferred embodiment of the present invention .
  • the wind tunnel comprises:
  • substantially vertical duct including a substantially vertical flight chamber 10, for housing a person who will fluctuate when hit by an air flow
  • a recirculation apparatus in fluidic communication with flight chamber 10, defining a substantially closed path for said air flow
  • blower device 14 for producing said air flow that will circulate between flight chamber 10 and the recirculation apparatus;
  • Said substantially vertical duct includes:
  • truncated cone portion 12 connected at the top to cylindrical portion 11, having the shape of an upward- diverging truncated cone.
  • flight chamber 10 comprises cylindrical portion 11 and truncated cone portion 12.
  • flight simulation the user can also gain access to the area designated by number 22, since no barriers are provided between said area 22 and truncated cone portion 12.
  • truncated cone portion 12 is a straight truncated cone, the bases of which are parallel to each other .
  • the air flow in the vertical duct, and hence in flight chamber 10, is ascending.
  • the vertical duct has a substantially straight vertical axis z-z.
  • the air flow runs through flight chamber 10 in a substantially axial, or vertical, direction.
  • Cylindrical portion 11 and truncated cone portion 12 are aligned with vertical axis z-z.
  • the cross-sections of cylindrical portion 11 and of truncated cone portion 12 are circular.
  • truncated cone portion 12 reduces the velocity of the fluid, resulting in less load losses and lower energy consumption .
  • the air circulates in the wind tunnel in clockwise direction, as indicated by dashed arrow 7.
  • the recirculation apparatus comprises a first duct 16 in fluidic communication with truncated cone portion 12 through an angular connection 18, which comprises deflecting means 20 (which may hereafter be referred to simply as “deflectors” 20) interposed between a pair of angular portions 22, 24, wherein at least one of said angular portions 22, 24 has diverging surfaces that diverge like truncated cone portion 12, so as to create a substantially continuous profile with said truncated cone portion 12.
  • angular connection 18 is a duct that can put the first duct 16 in fluidic communication with truncated cone portion 12.
  • Deflectors 20 are located in the inner of the angular connection 18.
  • Figure 5 shows, by way of example, a particular type of deflecting means 20, in particular associated with angular portion 22.
  • the particular deflecting means 20 illustrated therein is of the grid type .
  • the first angular portion 22 and truncated cone portion 12 create a continuous profile shaped like an (upward- diverging) truncated cone, wherein upper edge 22a of the first angular portion 22 lies in a plane that is not perpendicular to vertical axis z-z of flight chamber 10.
  • upper edge 22a has a substantially elliptical shape .
  • the second angular portion 24 has diverging surfaces with the same divergence angle as the first angular portion 22. Therefore, the assembly made up of portions 12, 22, 24 forms a diverging angular duct for the air flow, thanks to which the velocity of the fluid is reduced, thereby minimizing the load losses and hence the energy consumption.
  • a user's flight experience can occur in a volume with no discontinuities mainly due to cross-section changes or non-circular cross-sections. Also, it is possible to build a closed-circuit wind tunnel that is not very bulky.
  • first duct 16 extends along a longitudinal axis, and is inclined relative to flight chamber 10, and hence relative to the vertical duct. Therefore, angular connection 18 deflects the air flow exiting flight chamber 10 towards the first duct 16.
  • the wind tunnel can be made more efficient by promoting the passage of the air flow between the air duct located downstream of deflecting means 20 and the one located upstream of deflecting means 20.
  • angular connection 18 is not provided with deflecting means 20, therefore the first angular portion 22 and the second angular portion 24 are directly connected to each other.
  • the first duct 16 is substantially horizontal, and the recirculation apparatus further comprises:
  • the air flows through angular connection 18 into the first horizontal duct 16, and then into the second vertical duct 26 in a downward motion. Afterwards, the air flows into the horizontal lower duct 28, and finally into the vertical duct, where it arrives at flight chamber 10.
  • the ducts belonging to the particular wind tunnel illustrated herein are thus so arranged as to substantially form a parallelepipedon .
  • the first duct 16 is divergent with reference to the air flow. Load losses, and hence energy requirements, can thus be reduced even further.
  • the second vertical duct 26 is divergent with reference to the air flow.
  • the cross-section of the first duct 16 is substantially circular; load losses can thus be further reduced.
  • the cross-section through which the air flow will flow increases, possibly with short segments having a constant cross-section. In this way it is possible to reduce the load losses and avoid abrupt cross-section changes, thus minimizing the energy consumption.
  • the vertical duct comprises a tapered part 30 in fluidic communication with the lower part of cylindrical portion 11; the inner surface of tapered part 30 has, in its longitudinal section, a concave part 30a and a convex part 30b (see Figure 4) .
  • Said tapered part 30 becomes narrower, with particular reference to the air flow, towards cylindrical portion 11.
  • Tapered part 30 accelerates the velocity of the air that enters from below into flight chamber 10, in particular into cylindrical portion 11, in order to let the user fluctuate when the latter is hit by an air flow.
  • tapered part 30 is coaxial to vertical axis z-z, and the section shown in Figure 4 is cut along a plane including said vertical axis z-z.
  • Concave part 30a and convex part 30b, shown in Figure 4 meet at a saddle point designated as F.
  • the cross- section of tapered part 30 is substantially circular.
  • a first fitting 32 puts the first duct 16 in fluidic communication with the second vertical duct 26.
  • a second fitting 34 puts the second vertical duct 26 in fluidic communication with horizontal lower duct 28.
  • a third fitting 36 puts horizontal lower duct 28 in fluidic communication with the vertical duct, and therefore with flight chamber 10.
  • Fittings 32, 34, 36 have an angular shape and deflect the fluid.
  • such fittings 32, 34, 36 internally house respective deflecting means 20, which are advantageously of the same or an equivalent type as those used in angular connection 18.
  • deflecting means 20 comprise a plurality of fins secured to a support structure, which may be, for example, a peripheral support structure (e.g. having an elliptical, square, rectangular, circular, etc. shape) .
  • the fins may be curved to improve the deflection of the air flow.
  • blower device 14 is located in the second vertical duct 26. It may however be located in other parts of the wind tunnel. Also, a plurality of blower devices 14 may be employed, arranged in different zones of the wind tunnel, in accordance with the required aeraulic performance. For example, blower device 14 may be a single blower; a plurality of blowers may nevertheless be used, as well as other per se known apparatus .
  • Blower device 14 may be controlled via a control system; for instance, the control system may be able to control the act ivation/deactivation of blower device 14 according to an operator's commands issued, for example, from a remote control panel.
  • the control system may be able to control the operation of blower device 14 as a function of parameters read by sensor means associated with the wind tunnel.
  • flight chamber 10 comprises an air-permeable wall 40 that can be crossed by the air flow.
  • permeable wall 40 may be a grate, a net, a reticular wall or a perforated plate having holes of any shape and size, according to specific requirements.
  • permeable wall 40 lies in a plane substantially transversal to the vertical axis z-z of flight chamber 10.
  • permeable wall 40 also acts as a support plane, or floor, for the people within flight chamber 10, as well as for any objects.
  • Permeable wall 40 lies at the base of cylindrical portion 11, in particular between cylindrical portion 11 and tapered part 30.
  • the second permeable wall minimizes the risk that people or objects might by pushed by the air flow towards parts of the wind tunnel, such as, for example, the recirculation apparatus or blower device 14, thus avoiding the risk of accidents as well as the risk of malfunctioning or jamming of the wind tunnel itself.
  • the second permeable wall may consist of deflecting means 20.
  • the second permeable wall may be arranged between the portions designated by numbers 12 and 22. In these variant embodiments, therefore, permeable wall 40 and the second permeable wall delimit the region of flight chamber 10 in which a user can hover in a vertical or upward air flow for making a free-falling or parachuting simulation in safe conditions.
  • flight chamber 10 is at least partly made of transparent material, such as: glass, crystal, transparent plastic, polymethylmethacrylate (also known as Plexiglas), etc.
  • transparent material such as: glass, crystal, transparent plastic, polymethylmethacrylate (also known as Plexiglas), etc.
  • the transparent material is convenient because it offers the possibility of seeing through flight chamber 10; for example, it will allow people standing outside the wind tunnel to watch a user engaged in a free-falling or parachuting simulation within the wind tunnel.
  • a whole part of flight chamber 10 is made of transparent material, thus allowing 360-degree vision of the inside of chamber 10.
  • a segment comprised between two parts orthogonal to the main axis z-z, in which the vertical duct is made of transparent material.
  • cylindrical portion 11 and possibly also truncated cone portion 12 may be made of transparent material.
  • portions 11 and/or 12 have a windowed surface made of transparent material.
  • the wind tunnel comprises an access to allow the entry and exit of a person or an object into/from flight chamber 10.
  • Said access crosses, for example, cylindrical portion 11 and/or truncated cone portion 12, particularly in a substantially radial or transversal direction.
  • the access comprises only a door; or it may comprise a generic element for controlling the entry and exit of a person or an object into/from flight chamber 10, such as a shutter or a sliding door.
  • the door(s) may be of a per se known type, such as a single-wing door, a double-wing door, a shutter, etc.
  • the access is also made of transparent material.
  • the part of the wind tunnel which is comprised between the air-permeable walls is made of transparent material. More preferably, the access, which is also made of transparent material, is located between the permeable walls.

Abstract

L'invention concerne une soufflerie à flux de recirculation, en particulier pour des simulations de chute libre ou de parachutage, qui comprend : un conduit sensiblement vertical comprenant un caisson de simulation sensiblement vertical (10) pour loger une personne qui va osciller au moment où elle sera heurtée par un écoulement d'air; un appareil de recirculation (16, 26, 28, 18, 32, 34, 36) en communication fluidique avec le caisson de simulation (10), définissant un chemin sensiblement fermé pour l'écoulement d'air; et un ventilateur (14) pour générer l'écoulement d'air qui va circuler entre le caisson de simulation (10) et l'appareil de recirculation (16, 26, 28, 18, 32, 34, 36). Le conduit sensiblement vertical comprend : une partie cylindrique (11) ayant une section transversale circulaire; et une partie de cône tronqué (12), raccordée au niveau de la partie supérieure à la partie cylindrique (11), et ayant la forme d'un cône tronqué s'écartant vers le haut.
PCT/IB2016/054036 2015-07-07 2016-07-06 Soufflerie à flux de recirculation, en particulier pour simulations de chute libre ou de parachutage WO2017006251A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
ITUB2015A001891A ITUB20151891A1 (it) 2015-07-07 2015-07-07 Galleria del vento a flusso ricircolante, in particolare per effettuare simulazioni di caduta libera o paracadutismo.
IT102015000031324 2015-07-07

Publications (1)

Publication Number Publication Date
WO2017006251A1 true WO2017006251A1 (fr) 2017-01-12

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/IB2016/054036 WO2017006251A1 (fr) 2015-07-07 2016-07-06 Soufflerie à flux de recirculation, en particulier pour simulations de chute libre ou de parachutage

Country Status (2)

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IT (1) ITUB20151891A1 (fr)
WO (1) WO2017006251A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3671170A1 (fr) * 2018-12-19 2020-06-24 aem - GmbH Agencement de réseau, canal d'écoulement doté de l'agencement de réseau et écarteur
US11707689B2 (en) 2018-11-16 2023-07-25 Ifly Holdings, Llc Recirculating vertical wind tunnel

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110100109A1 (en) * 2009-10-29 2011-05-05 Korea Institute Of Energy Research Compact Wind Tunnel Instrument
US8668497B2 (en) * 2008-09-11 2014-03-11 Indoor Skydiving Bottrop Gmbh Free fall simulator
US9045232B1 (en) * 2013-03-14 2015-06-02 Timothy A. Burke Transportable system for simulating free fall in air

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8668497B2 (en) * 2008-09-11 2014-03-11 Indoor Skydiving Bottrop Gmbh Free fall simulator
US20110100109A1 (en) * 2009-10-29 2011-05-05 Korea Institute Of Energy Research Compact Wind Tunnel Instrument
US9045232B1 (en) * 2013-03-14 2015-06-02 Timothy A. Burke Transportable system for simulating free fall in air

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11707689B2 (en) 2018-11-16 2023-07-25 Ifly Holdings, Llc Recirculating vertical wind tunnel
EP3671170A1 (fr) * 2018-12-19 2020-06-24 aem - GmbH Agencement de réseau, canal d'écoulement doté de l'agencement de réseau et écarteur

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Publication number Publication date
ITUB20151891A1 (it) 2017-01-07

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