FR2731202A1 - Reduction of parachute sail surface - Google Patents
Reduction of parachute sail surface Download PDFInfo
- Publication number
- FR2731202A1 FR2731202A1 FR9502671A FR9502671A FR2731202A1 FR 2731202 A1 FR2731202 A1 FR 2731202A1 FR 9502671 A FR9502671 A FR 9502671A FR 9502671 A FR9502671 A FR 9502671A FR 2731202 A1 FR2731202 A1 FR 2731202A1
- Authority
- FR
- France
- Prior art keywords
- halyards
- pulleys
- partitions
- reduction
- reduction zone
- 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.)
- Granted
Links
- 238000005192 partition Methods 0.000 claims abstract description 13
- 230000000903 blocking effect Effects 0.000 claims description 3
- 238000004873 anchoring Methods 0.000 abstract description 2
- 210000005069 ears Anatomy 0.000 description 2
- 206010040954 Skin wrinkling Diseases 0.000 description 1
- 230000002159 abnormal effect Effects 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 230000002146 bilateral effect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D17/00—Parachutes
- B64D17/02—Canopy arrangement or construction
- B64D17/025—Canopy arrangement or construction for gliding chutes
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
Description
La présente invention concerne un dispositif de réduction, en vol, de la surface des ailes souples double surface, de type Parapente et Parachute, dans le but d'augsenter leur taux de chute ainsi que leur vitesse
Air.The present invention relates to a device for reducing, in flight, the surface of flexible double-surface wings, of the paraglider and parachute type, with the aim of increasing their fall rate as well as their speed.
Air.
Cette manoeuvre est babituellenent réalisée par une fermeture bilatérale des extrémités de l'aile, grâce å une traction sur les suspentes extérieures du groupe avant (manoeuvre dite des "oreilles"). Le résultat est effectif sur le taux de chute nais n'induit pas d'accélération car les parties fermées de l'aile génèrent une trainée importante. This maneuver is usually carried out by a bilateral closure of the ends of the wing, thanks to a traction on the external lines of the front group (so-called "ears" maneuver). The result is effective on the fall rate but does not induce acceleration because the closed parts of the wing generate a large drag.
Le dispositif selon l'invention permet de réduire la surface de 11 aile par une réduction, en vol, de son envergure. Cette réduction s'opère par un rapprochenent des cloisons inter-alvéoles (4) d'une ou plusieurs parties de l'aile grace å un ensemble de drisses et de poulies internes au profil. The device according to the invention makes it possible to reduce the area of 11 wing by reducing, in flight, its wingspan. This reduction is effected by bringing the inter-cell partitions (4) closer to one or more parts of the wing thanks to a set of halyards and pulleys internal to the profile.
Sur les deux cloisons (4) délimitant l'alvéole ou l'ensemble d'al véoles concernées par le dispositif (zone de réduction) sont aménagés les systènes d'ancrage (3) des poulies et des drisses.Ces ancrages sont répartis régulièrement sur la corde de la cloison. Leur nombre varie selon la dinension de celle-ci.Les ancrages de l'une de ces cloisons re çoivent un oeillet (6) pour la fixation de l'extrémité des drisses.Ceux de l'autre cloison recoivent des poulies (2).Les drisses (1) sont ancrées à ces oeillets puis traversent les cloisons de la zone de réduction par des orifices (7) pour rejoindre les poulies qui leur correspondent puis traversent l'intrados de l'aile (par des orifices) pour rejoindre un dispositif de blocage (taquet coinceur ou autre) solidaire du harnais du pilote ou des élévateurs (5). Les drisses d'une même zone de réduction sont réunies en patte d'oie sur une seule afin d'obtenir une traction et un blocage sinultané. On the two partitions (4) delimiting the cell or the set of cells concerned by the device (reduction zone) are fitted the anchoring systems (3) of the pulleys and the halyards. These anchors are distributed regularly over the partition cord. Their number varies according to the size of the latter. The anchors of one of these partitions receive an eyelet (6) for fixing the end of the halyards. Those of the other partition receive pulleys (2). The halyards (1) are anchored to these eyelets then pass through the partitions of the reduction zone through orifices (7) to join the pulleys which correspond to them then cross the underside of the wing (through orifices) to join a device blocking device (cam cleat or other) secured to the pilot's harness or risers (5). The halyards of the same reduction zone are joined in crow's feet on a single one in order to obtain a traction and a blocking sinultaneous.
En vol nornal le dispositif n'est pas activé et la ou les drisses de commande sont détendues. Lorsque le pilote désire augmenter le taux de chute et (ou) la vitesse, il effectue une traction sur la (ou les) drisse(s) de conazxle qui provoque un repliage sur elle ne-ne de la zone de réduction. La drisse est alors maintenue en position sur le taquet coinceur.Le repliage des alvéoles sur elles-neses n'engendre qu'une légère a;ientation de la trainée et l'aile, dont la charge alaire augmente, accélère. In normal flight, the device is not activated and the control halyard (s) are relaxed. When the pilot wishes to increase the fall rate and / or the speed, he pulls on the conazxle halyard (s) which causes the reduction zone to fold back onto it. The halyard is then held in position on the cleat cleat. The folding of the cells on them-neses generates only a slight orientation of the drag and the wing, whose wing loading increases, accelerates.
Si la traction nécéssaire s'avère trop isportante, un mouflage peut etre rajouté afin de dénultiplier l'effort. If the necessary traction proves to be too important, a hauling can be added in order to increase the effort.
Si la ou les zones de réduction sont aménagées au centre de la voute de l'aile, les connandes de pilotage (les freins) conservent leur éfficacité. Le pilote se trouvant en situation de pilotage anormal sur une aile moins surfacée: Ce qui n'est pas le cas avec la technique des "oreilles' qui condamne les freins. If the reduction zone (s) are located in the center of the arch of the wing, the steering elements (the brakes) retain their effectiveness. The pilot being in an abnormal piloting situation on a less surfaced wing: This is not the case with the technique of "ears" which condemns the brakes.
Pour revenir en vol nornal, le pilote libère la (ou les) drisses du taquet et les alvéoles pliées se redéploient grace t la pression interne du profil. To return to normal flight, the pilot releases the halyard (s) from the cleat and the folded alveoli are redeployed thanks to the internal pressure of the profile.
Les dessins ci-annexés illustrent l'invention:
La figure i représente, en coupe frontale, l'aile en vol nornal (A) et en vol rapide (B) celle-ci étant punie de deux zones de réduction en position centrale.The attached drawings illustrate the invention:
FIG. I represents, in frontal section, the wing in nominal flight (A) and in rapid flight (B) the latter being punished with two reduction zones in the central position.
La figure 2 représente, en coupe frontale,un exemple de dispositif concernant deux alvéoles. drisse détendue. FIG. 2 shows, in front section, an example of a device relating to two cells. relaxed halyard.
La figure 3 représente, en coupe frontale, le dispositif précédent drisse tendue. Figure 3 shows, in front section, the previous device halyard taut.
La figure 4 représente, une perspective en éclaté, du dispositif précédent, drisse détendue. Figure 4 shows an exploded perspective of the previous device, relaxed halyard.
Claims (5)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR9502671A FR2731202B1 (en) | 1995-03-02 | 1995-03-02 | SURFACE REDUCTION DEVICE FOR FLEXIBLE DOUBLE SURFACE WINGS |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR9502671A FR2731202B1 (en) | 1995-03-02 | 1995-03-02 | SURFACE REDUCTION DEVICE FOR FLEXIBLE DOUBLE SURFACE WINGS |
Publications (2)
Publication Number | Publication Date |
---|---|
FR2731202A1 true FR2731202A1 (en) | 1996-09-06 |
FR2731202B1 FR2731202B1 (en) | 1997-06-27 |
Family
ID=9476838
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
FR9502671A Expired - Fee Related FR2731202B1 (en) | 1995-03-02 | 1995-03-02 | SURFACE REDUCTION DEVICE FOR FLEXIBLE DOUBLE SURFACE WINGS |
Country Status (1)
Country | Link |
---|---|
FR (1) | FR2731202B1 (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2004037639A1 (en) * | 2002-10-21 | 2004-05-06 | Arnaud Ballu | Power management system for kite sail |
WO2017151483A1 (en) | 2016-03-04 | 2017-09-08 | Airborne Systems Na Inc. | Glide modulator system and method for a ram air parachute |
CN108438234A (en) * | 2018-05-18 | 2018-08-24 | 深圳市百川融创科技有限公司 | Double-vane umbrella |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN109250123B (en) * | 2018-10-19 | 2021-11-16 | 航宇救生装备有限公司 | Slit type inflatable ram parafoil |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2384127A (en) * | 1944-01-17 | 1945-09-04 | Albert R Nailor | Parachute |
US4065079A (en) * | 1975-03-05 | 1977-12-27 | Irvin Great Britain Limited | Parachute reefing device |
US4540145A (en) * | 1984-08-27 | 1985-09-10 | The United States Of America As Represented By The Secretary Of The Navy | Reefing system |
US4846423A (en) * | 1987-11-23 | 1989-07-11 | Pioneer Aerospace Corporation | Gliding wing parachute apparatus with staged reefing deployment means |
-
1995
- 1995-03-02 FR FR9502671A patent/FR2731202B1/en not_active Expired - Fee Related
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2384127A (en) * | 1944-01-17 | 1945-09-04 | Albert R Nailor | Parachute |
US4065079A (en) * | 1975-03-05 | 1977-12-27 | Irvin Great Britain Limited | Parachute reefing device |
US4540145A (en) * | 1984-08-27 | 1985-09-10 | The United States Of America As Represented By The Secretary Of The Navy | Reefing system |
US4846423A (en) * | 1987-11-23 | 1989-07-11 | Pioneer Aerospace Corporation | Gliding wing parachute apparatus with staged reefing deployment means |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2004037639A1 (en) * | 2002-10-21 | 2004-05-06 | Arnaud Ballu | Power management system for kite sail |
WO2017151483A1 (en) | 2016-03-04 | 2017-09-08 | Airborne Systems Na Inc. | Glide modulator system and method for a ram air parachute |
EP3423355A4 (en) * | 2016-03-04 | 2019-09-11 | Airborne Systems NA Inc. | Glide modulator system and method for a ram air parachute |
AU2017225669B2 (en) * | 2016-03-04 | 2022-03-31 | Airborne Systems Na Inc. | Glide modulator system and method for a ram air parachute |
CN108438234A (en) * | 2018-05-18 | 2018-08-24 | 深圳市百川融创科技有限公司 | Double-vane umbrella |
Also Published As
Publication number | Publication date |
---|---|
FR2731202B1 (en) | 1997-06-27 |
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Legal Events
Date | Code | Title | Description |
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ST | Notification of lapse |