EP2398979A2 - Support pneumatique incurvé - Google Patents

Support pneumatique incurvé

Info

Publication number
EP2398979A2
EP2398979A2 EP10708088A EP10708088A EP2398979A2 EP 2398979 A2 EP2398979 A2 EP 2398979A2 EP 10708088 A EP10708088 A EP 10708088A EP 10708088 A EP10708088 A EP 10708088A EP 2398979 A2 EP2398979 A2 EP 2398979A2
Authority
EP
European Patent Office
Prior art keywords
web
carrier
tension
pressure
pneumatic
Prior art date
Legal status (The legal status 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 status listed.)
Withdrawn
Application number
EP10708088A
Other languages
German (de)
English (en)
Inventor
Joep Breuer
Rolf Luchsinger
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Prospective Concepts AG
EMPA
Original Assignee
Prospective Concepts AG
EMPA
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 Prospective Concepts AG, EMPA filed Critical Prospective Concepts AG
Publication of EP2398979A2 publication Critical patent/EP2398979A2/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • E—FIXED CONSTRUCTIONS
    • E04—BUILDING
    • E04H—BUILDINGS OR LIKE STRUCTURES FOR PARTICULAR PURPOSES; SWIMMING OR SPLASH BATHS OR POOLS; MASTS; FENCING; TENTS OR CANOPIES, IN GENERAL
    • E04H15/00—Tents or canopies, in general
    • E04H15/20—Tents or canopies, in general inflatable, e.g. shaped, strengthened or supported by fluid pressure
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49826—Assembling or joining

Definitions

  • the present invention relates to an elongated, curved pneumatic carrier according to the preamble of claim 1.
  • Elongate pneumatic supports are known in the art. They are characterized by a straight, usually cylindrical or spindle-shaped inflatable body, wherein longitudinally along the body extends a pressure member which is connected at the end with flexible tension members, which in turn are helically wound around the body, such as Z.Bsp WO 01/73245 shows.
  • Such carriers have the advantage that they can carry considerable loads in relation to their weight (for example, 2 such carriers weighing approximately 70 kg each and 8 m long are capable of supporting a car as an inflatable bridge) and that they are easily transportable in the folded state.
  • the assembly is extremely simple: thanks to its rigidity, the carrier can basically simply be placed on the bearing points with its knots.
  • a carrier toroidal so that the pressure rod then forms a circle with at least one node.
  • a carrier can accommodate radially directed against its center load.
  • the convex (ie the load attacking side) of the carrier is suitable for this, but not the concave side, because there the Load attack comes from a direction for which it is not trained.
  • a carrier can be used only for the special case of all around uniformly and constantly attacking load. If such a carrier can receive load from one direction, nodes resting on a support must be provided on both sides of the loaded section of the carrier. Then the rest of the area of the carrier is not, and thus not unduly burdened, as would be the case without the additional nodes. In other words, then the remaining area of the carrier is not necessary and can be omitted.
  • WO 2007/071100 shows a semicircular curved, pneumatic carrier (Fig. 10), which has, however, by parallel struts a shaping solid internal framework and thus "pre-stabilized without pneumatic hollow body" is. This means that the conceptual advantages of pneumatic supports are no longer a factor.
  • WO 2005/007991 a spindle-shaped pneumatic support is shown, with opposing pressure and tension member, wherein "push rod 3 and tension element 4""in the plane of action of the load vector" lie.
  • the pulling member is converted into a pressure / tension member.
  • this carrier has thus a shaping framework in the form of pressure / tension members, which determines the shape of the wearer with or without pressure in the body.
  • Missiles such as dragons are increasingly being used today, with the traction transferred by the lines being used technically. So for example. for ships such as the MS Beluga SkySails, a container cargo ship of approx. 140 m in length, which has an auxiliary drive in the form of a towing kite, which flies at wind speeds of 3 to 8 Beaufort at a height of several 100 m. Land-supported dragons can be used for alternative energy generation.
  • kites it is always advantageous to keep such kites at a certain height, which can also be one or more kilometers. Then the additional irregularities of the wind flow, which are given by the ground level, are eliminated; at a certain height this is considerably more even than near the ground. Furthermore, the wind speeds are also generally higher at a certain altitude (and thus also the energy content of the wind).
  • a role not to be underestimated in a higher-flying kite is played by the kite lines or their cross-section, which can limit the achievable flying height.
  • simulation models show that for a dragon with a span of 8 m (which then has an area of possibly li m 2 ) and lines with a diameter of 1.0 mm, a flying height of 1 km is difficult to overcome.
  • a line already has a length of about 2 km, as the dragon can not of course stand vertically above the anchor point.
  • the cross-sectional area of the leash is 2 m 2 .
  • Two such lines, which attack laterally at the wing tips of the kite have a cross-sectional area of 4 m 2 , which acts only braking and produces no buoyancy.
  • Leashes of the dragon can be controlled. So for example. in the kites used in water sports, the edge of an inflatable, the semi-circular
  • Contour contour following inflatable bead This bead is composed of straight cylinder sections in the manner of the polygon and represents the
  • Control of a kite is especially necessary for compensation or correction of dangerous flight positions due to local wind disturbances. manoeuvrable because some dragons, due to their design, are aerodynamically unstable and thus need control organs or are to be built so that they have defined other flight characteristics. For example, if control organs are carried in a platform suspended below the kite, as is the case with the MS Beluga SkySails, the kite's usable power is reduced. Are the control organs like the conventional kite on the ground (eg in the shape of the kite pilot) are several lines over the full length, with the correspondingly disadvantageous large cross-sectional area unavoidable.
  • An aerodynamically stable dragon which is then able to fly safely with only one leash, must be provided with a correspondingly defined surface shape.
  • the object of the present invention to provide a construction for the construction of kites with defined flight characteristics such as aerodynamic stability and / or aerodynamic efficiency, which increases the weight of the missile but only slightly.
  • the carrier is at least partially curved, it can be used for the construction z.Bsp. of a kite, since its shape can be tuned to the desired aerodynamic conditions, giving the kite the defined flight characteristics.
  • this shaping is produced by the pattern of the shell, eliminating the otherwise necessary for shaping inner truss elements or outside the carrier extending, forming tension elements (which in turn would then adversely affect the flow of forces in the carrier).
  • the position of the pressure member can also be determined with the curvature, so that the carrier according to the invention can absorb irregularly acting load from various directions, without that more material must be used or external abutments must be provided.
  • a carrier is thus available that allows the desired design of a kite without its construction weight being increased significantly.
  • FIG. 1 is a view of the inventive pneumatic carriers existing structure of a dragon, wherein one half of the symmetrical structure is shown,
  • FIG. 2a and 2b is a top view and a front view of the structure of Fig. 1,
  • Fig. 3 shows the spar of the dragon with transparently illustrated shell, so that the course of the web is visible
  • Fig. 4 shows the arrangement of Rg. 3 in yet another view, in which the course of the tension member is visible, and
  • FIGS. 5 a to c show a pattern of the arrangement of FIG. 1.
  • FIG. 1 the structure of the left half of a kite 1 is shown, with its right half being symmetrical with respect to it and therefore being used to disengage it. the figure is omitted.
  • Shown is a trained as a spar 2 carrier, which forms the front edge of the kite 1, and a longitudinal beam 3, which is connected to the spar 2 and spans the indicated by the auxiliary lines 4 supporting surface 5 of the kite. Further illustrated are from the spar 2 rearwardly projecting subcarrier 6.
  • the bearing surface 5 can be generated by a covering, which is placed over the spar 2, the subcarrier 6 and the longitudinal member 3. This can be done by the skilled person in a suitable manner.
  • the person skilled in the art can determine the resulting shape of the supporting surface 5 and, in turn, the shape of the spar 2, the carrier 6 and the longitudinal member 3.
  • the spar 2 upwards and backwards, so twice curved, but so that it is always directed for lowest flow resistance with its narrow side 8 to the front.
  • the subcarriers 6 are formed at the top of the desired surface 5 accordingly.
  • the spar 2, the auxiliary carrier 6 and the longitudinal member 3 form a framework of individual pneumatic carriers, which is suitable to carry the fabric of the kite 1.
  • the spar 2, the longitudinal beam 3 and the subcarrier 6 are formed as elongated, curved pneumatic carrier, each with a substantially inelastic sheath 9, with a gas under slight overpressure (z.Bsp., An operating pressure of 5 to 10 kPa) is filled.
  • the sheath 9 is made of a less elastic, flexible material, preferably a fabric, which is particularly preferably gas-tight.
  • inflatable bladders of gas-tight material may be placed in the envelope 9, which as such may be stretchable; then the sheath 9 is not gas-tight
  • a suitable material is a PU coated ripstop fabric, such as that marketed under the trademark ICAREX.
  • the spar 2 is closed at the end, so that it can be placed under operating pressure and then assumes the shape shown in the figures.
  • the shape shown corresponds to the CAD representation of a dragon with 8 m span, which transmits a lift of about 100 kg over the line corresponding to about 100 kg of tension.
  • pressure member 22 and tension member 23 specifies the subject-5 man according to the anticipated in-flight load attack, this load attack can also include the forces occurring in unwanted attitude.
  • this load attack can also include the forces occurring in unwanted attitude.
  • the course of the web 20 and the arrangement of the pressure member 22 and the tension member 23 is aligned with the maximum forces, namely such that they are then as much as possible in the Hum0 of the web.
  • the curvature of the spar 2 (and the other pneumatic supports) is predetermined in view of extraordinary load, but this curvature is not optimal in view of the normal attitude.
  • the carrier or spar 2 or the longitudinal member 3 and the auxiliary carrier 6) are to be designed for very high load peaks, experiments are indicated in terms of stability, which can be carried out easily by the person skilled in the art.
  • the tension member 23 can be omitted as such in the web, since the connection point between the web and the pressure-loaded shell, usually a seam, corresponds to a reinforced point in the web (and also suitable with respect to the normal Seam can be reinforced).
  • a reinforced seam absorbs a low tensile load and therefore fulfills the function of a tension member 23.
  • Such reinforcements are preferably provided in combination with a tension member 23.
  • the tension member 23 may be replaced by a tension / compression member (which can then also absorb tension, but acts as a compression member when loaded from the opposite direction). Such a replacement can in principle be made in all embodiments of the inventive curved pneumatic support.
  • the arrangement shown in the figure is an example of a missile; for other, any applications, the pneumatic support may have a different curvature and be designed for a different predetermined, general load distribution.
  • Figures 2a and 2b show the structure of Figure 1, but in a front view ( Figure 2a) and in a top view ( Figure 2b).
  • the reference numerals denote the same elements as in Figure 1. It can be seen, the plane of symmetry 24 and the curvature upward of the spar 2 (Figure 2a) and in addition to the Holm 2 of the rear end 25 of the given by the covering supporting surface 5 and the curvature of the spar 2 to the rear ( Figure 2b).
  • Figure 3 shows the spar 2 of Figure 1 in a view from the top side, slightly offset from the rear.
  • the outer shell 9 of the spar 2 is shown transparently and indicated by auxiliary lines.
  • the lines 26 to 30 denote different cross sections of the operating pressure shell 9, and thus of the spar 2, from the inside to the outside; 26 is the cross section of the spar 2 in the plane of symmetry which divides the spar and the longitudinal beam 3 in FIG. 30 is the cross section at the outer end of the spar 2.
  • auxiliary lines 31 and 32 which extend along the sides of the spar 2, from its center located in the plane of symmetry to the outer end of the spar 2.
  • the figure shows the web 20 with its upper longitudinal edge 21, its lower longitudinal edge 36 and its outer end 37. It can be seen that the curved shape of the web 20, which extends on the one hand upwards and to the rear, and on the other hand additionally rotated about its longitudinal axis, so that in cross-section 26 its against the rear surface 39 and in cross-section 28 its directed towards the front surface 40 appears.
  • the pressure member 22 extends laterally to the node 42 on which the tension member 23 engages.
  • the node 42 outwardly projecting portion of the spar 2 is less stressed in flight and serves as an additional lanyard against shocks during the landing of the kite 1. Due to the inventive design of the beam 2 while this can absorb the operational high stress; the sufficient dimensioning of the pressure member 22 but sufficient (deliberately, due to the optimized lightweight construction) by no means to survive hard shocks on landing unscathed. If such protection is not desired, the node 42 can be placed at the end of the pneumatic support, here the spar 2.
  • the carrier may this sections also slightly adjacent to the longitudinal edge 35, ie outside the web 20 in the shell 9, in which case the wall portion between the tension member 23 and the web 20 has a stabilizing effect, ie stress in the web 20 transmits to the pressure member 22.
  • the pressure member 22 is then assigned to the respective longitudinal edge 35 of the web 20 is still operable.
  • Figure 4 shows the spar 2 of Figure 1 with the course of the web 20, the pressure member 22 and the tension member 23.
  • the tension member 23 extends over a large length of the web 20 in this and only shortly before the cross section 26 in the longitudinal edge 36 passes.
  • the course of the tension member depends on the predetermined load of the spar 2 and can - if necessary by experiments - be optimized by the expert.
  • a plurality of webs may be provided, either adjacent to the web passing through its length, or in sections one behind the other, such that the pneumatic support is optimally tuned to the predetermined load case with different sized load attacks from different directions.
  • Side by side running webs (with each associated pressure and tension member) give the web z.Bsp. Stabilizing against load attack from different directions at the same place, or allowing for a curvature of one web unfavorable in this section (caused by the conditions in another section) to be compensated by a more favorable curvature of the other web.
  • webs arranged in sections one behind the other can be provided if pressure loading (or no significant load at all) occurs only in its longitudinal axis in a straight section of the carrier.
  • pneumatic supports not only the spar 2, but all the pneumatic supports (according to the embodiment shown in Fig. 1, the longitudinal support 3 and the Auxiliary carrier 6) are designed as described above.
  • pneumatic supports as exemplified in FIG. 1, can be assembled to form a framework. Then there is not a truss which is arranged in a pneumatic support and supports it (thus the above-described state of the art), but a truss formed from pneumatic supports.
  • a truss node in a truss of pneumatic supports is preferably designed such that a support is partially penetrated end by a running in another direction, other carrier, as shown in Figure 1 by way of example with reference to the subcarrier 6 and this end-side penetrating beam 2.
  • the attachment is preferably carried out by sewing the abutting covers of the respective pneumatic carrier.
  • the pressure and the tension member of the carrier, which is penetrated, can then be determined with the adjoining the shell of the other carrier end to this suitably, z.Bsp. by suturing in a bag arranged on this sleeve. It is also possible to connect the pressure member with the pressure member of the piercing carrier. Such a framework is surprisingly stiff.
  • the inventive curved pneumatic support can, as described in more detail in connection with Figure 1, designed according to a predetermined load and in its shape, including the course of the web and the compression and tension member determined.
  • CAD then the development of the carrier can be displayed in the plane, resulting in a pattern for the shell, ie the body of the wearer and the associated web. If this pattern is produced and stitched together for the manufacture of a carrier, the predetermined curvature of the at least one curved carrier section results under operating pressure.
  • the somewhat flexurally elastic pressure member follows this curvature since, even at low operating pressure, considerable forces are created which pre-stress the shell and the web.
  • a pre-bent pressure member which is made of bendable carbon fiber tube, for example
  • this can not withstand the biasing forces given by the operating pressure and then takes the predetermined position.
  • the pressure member is to absorb substantially compressive forces, but no or only minor bending moments (it is protected at the location of the web against kinking through this and the biased shell) it can be correspondingly weak dimensioned, with the advantage that its weight the weight of the pneumatic Carrier only slightly, but still significantly increased its capacity.
  • a tension member is replaced by a pressure member as described above.
  • the flexural elasticity of the pressure member allows a bending elasticity of the curved pneumatic support, and here the supporting surface 5 of the kite 1, which is necessary for a missile and may also be favorable or necessary for other applications.
  • the development is disassembled, so that a cutting pattern of several individual parts is produced, which the skilled worker designed in such a way that the assembly in the production is facilitated.
  • the course of the web results in the pneumatic support on the one hand by its cutting pattern and on the other hand by the course of the connection points with the pressurized walls.
  • FIGS. 5a, 5b and 5c show the CAD pattern of the left half of the kite 1 shown in FIG. 1 and its homly 2, respectively.
  • FIG. 5a schematically shows the position of the individual cut pattern parts 40 to 50 of FIGS. 5b and 5c. Shown is a cross-section 26,27 ( Figure 3) with the there sewn cut pattern parts 40 to 50, wherein a seam is indicated by the short, dashed lines. Only three pattern pieces, namely the pattern portion 45 for the web 20, and a stitched on this top and forward cutting pattern portion 46 and a sewed down to this, directed backwards ThomasGermanteil 40 extend over the entire length of the part shown in FIG Holms 2.
  • the other sectional pattern parts 41, 42 and 47, 49 extend outward from the center of the spar 2 (ie, from the plane of symmetry 24), in which case one in each case further ThomasGermanteil 43,44 and 48,50 connects and extends to the outer end of the spar 2.
  • the double or triple lines of the pattern pieces 40 to 50 indicate the overlapping areas for the seams; the simple lines the places where the subcarrier 6 and the side member 3 connect to the spar 2.

Landscapes

  • Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Civil Engineering (AREA)
  • Structural Engineering (AREA)
  • Tents Or Canopies (AREA)
  • Mattresses And Other Support Structures For Chairs And Beds (AREA)

Abstract

L'invention concerne un support pneumatique incurvé comportant une enveloppe gonflable traversée sur sa longueur par un élément de liaison sous pression de service, cet élément comportant à son tour un élément de pression et un élément de tension. La courbure du support est prédéfinie par son utilisation et elle est générée en fonction du modèle de l'enveloppe et de l'élément de liaison.
EP10708088A 2009-02-17 2010-02-17 Support pneumatique incurvé Withdrawn EP2398979A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH00248/09A CH700461A2 (de) 2009-02-17 2009-02-17 Gekrümmter pneumatischer Träger.
PCT/CH2010/000042 WO2010094145A2 (fr) 2009-02-17 2010-02-17 Support pneumatique incurvé

Publications (1)

Publication Number Publication Date
EP2398979A2 true EP2398979A2 (fr) 2011-12-28

Family

ID=42352055

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10708088A Withdrawn EP2398979A2 (fr) 2009-02-17 2010-02-17 Support pneumatique incurvé

Country Status (7)

Country Link
US (1) US20120061516A1 (fr)
EP (1) EP2398979A2 (fr)
CN (1) CN102695840A (fr)
CA (1) CA2752548A1 (fr)
CH (1) CH700461A2 (fr)
WO (1) WO2010094145A2 (fr)
ZA (1) ZA201106037B (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ES2371518T3 (es) * 2007-11-19 2012-01-04 Prospective Concepts Ag Soporte neumático plegable.
CH706134A1 (de) 2012-02-22 2013-08-30 Prospective Concepts Ag Tragflügel aus flexiblem Material.
US11413491B2 (en) 2013-09-04 2022-08-16 Gonza Llc Neck exercise device and system

Family Cites Families (20)

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Publication number Priority date Publication date Assignee Title
US2191374A (en) * 1936-10-26 1940-02-20 Dixon Henry Secretan Collapsible pneumatic structure
US2886265A (en) * 1956-02-10 1959-05-12 Darrell L Ritter Light weight pneumatic airplane
US4102519A (en) * 1977-05-11 1978-07-25 The United States Of America As Represented By The Secretary Of The Air Force Variable lift inflatable airfoil for tethered balloons
FR2684408B1 (fr) * 1991-11-29 1996-09-27 Spironef Ind Voute gonflable.
CN1032833C (zh) * 1992-12-26 1996-09-18 天津纺织工学院 中子和γ射线辐射屏蔽材料
US5421128A (en) * 1994-01-14 1995-06-06 Sharpless; Garrett C. Curved, inflated, tubular beam
US5735083A (en) * 1995-04-21 1998-04-07 Brown; Glen J. Braided airbeam structure
JPH11512998A (ja) * 1996-07-18 1999-11-09 プロスペクテイブ コンセプツ アクチエンゲゼルシヤフト 固定翼航空機用空気入り適応翼
US5677023A (en) * 1996-10-10 1997-10-14 Brown; Glen J. Reinforced fabric inflatable tube
US6543730B2 (en) 2000-03-27 2003-04-08 Mauro Pedretti Pneumatic structural element
US6463699B1 (en) * 2001-03-23 2002-10-15 Obi Corporation Air beam construction using differential pressure chambers
US6860218B2 (en) * 2001-04-11 2005-03-01 Albany International Corp. Flexible fluid containment vessel
DE502004000889D1 (de) * 2003-03-21 2006-08-10 Prospective Concepts Ag Auftriebskörper für ein luftschiff
WO2005007991A1 (fr) * 2003-07-18 2005-01-27 Prospective Concepts Ag Support pneumatique
EP1660740B1 (fr) * 2003-08-27 2008-01-09 Prospective Concepts AG Structure porteuse en suspension a sustentation aerostatique
CA2543798C (fr) * 2003-11-04 2012-09-25 Prospective Concepts Ag Structure pneumatique plane
CH704442B1 (de) * 2005-12-23 2012-08-15 Prospective Concepts Ag Pneumatisches Bauelement.
WO2007071100A1 (fr) 2005-12-23 2007-06-28 Prospective Concepts Ag Element de construction pneumatique et toit construit a partir de celui-ci
CH705206B1 (de) * 2006-06-23 2012-11-30 Prospective Concepts Ag Pneumatische Tragstruktur.
ES2537182T3 (es) * 2011-03-31 2015-06-03 Lta Corporation Aeronave que incluye estructuras aerodinámicas

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Title
See references of WO2010094145A2 *

Also Published As

Publication number Publication date
ZA201106037B (en) 2015-05-27
US20120061516A1 (en) 2012-03-15
CH700461A2 (de) 2010-08-31
WO2010094145A3 (fr) 2012-06-14
CN102695840A (zh) 2012-09-26
CA2752548A1 (fr) 2010-08-26
WO2010094145A2 (fr) 2010-08-26

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