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WO2001070571A1 - Parachute avec caissons gonflables - Google Patents

Parachute avec caissons gonflables Download PDF

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Publication number
WO2001070571A1
WO2001070571A1 PCT/US2001/008391 US0108391W WO0170571A1 WO 2001070571 A1 WO2001070571 A1 WO 2001070571A1 US 0108391 W US0108391 W US 0108391W WO 0170571 A1 WO0170571 A1 WO 0170571A1
Authority
WO
WIPO (PCT)
Prior art keywords
canopy
flying device
parachute
wing
enclosure
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.)
Ceased
Application number
PCT/US2001/008391
Other languages
English (en)
Inventor
Carl K. Towley
Gordon Balena
Greg Olson
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Priority to AU2001247470A priority Critical patent/AU2001247470A1/en
Publication of WO2001070571A1 publication Critical patent/WO2001070571A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface 
    • B64C25/54—Floats
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C31/00—Aircraft intended to be sustained without power plant; Powered hang-glider-type aircraft; Microlight-type aircraft
    • B64C31/028—Hang-glider-type aircraft; Microlight-type aircraft
    • B64C31/036—Hang-glider-type aircraft; Microlight-type aircraft having parachute-type wing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C35/00—Flying-boats; Seaplanes
    • 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
    • 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
    • B64D17/22—Load suspension
    • B64D17/34—Load suspension adapted to control direction or rate of descent
    • 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
    • B64D17/22—Load suspension
    • B64D17/34—Load suspension adapted to control direction or rate of descent
    • B64D17/343—Load suspension adapted to control direction or rate of descent by reefing means
    • 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
    • B64D17/62—Deployment
    • B64D17/72—Deployment by explosive or inflatable means

Definitions

  • the present invention relates to a flying device incorporating a parachute.
  • Parachutes have developed from their origins in enabling airmen to descend from an aircraft in flight. Originally they employed symmetrical canopies and could not be directed in forwards flight. Next, by omitting certain panels in the canopy they could be steered during descent, to a considerable extent.
  • wing parachutes that is to say double canopy parachutes with fore and aft cells between the canopies, which are filled with air to inflate the parachute into an aerofoil. Forward motion increases the lift from the canopy, so that this typ of parachute has a slow rate of descent and can indeed be used as a hang glider.
  • wing parachute is herein called a "wing parachute”.
  • a difficulty with towing of a parachute is the initial lift off the ground, or indeed water. Dragging the canopy can damage it. Pulling it through the water wets it and worse, it can act as a drogue, possibly be damaged and be difficult to inflate with air.
  • the object of the invention is to provide an improved flying device incorporating a parachute.
  • a flying device as such, namely a device ready for a user to fly with.
  • a flying device comprises: • a parachute, including a canopy and shroud lines, • a support for the user connected to the shroud lines and
  • the user can be towed and lifted - once the canopy has fully deployed - without it dragging on the ground or in the water.
  • the device may be adapted for towing behind a vehicle such as a car or a boat, in which case, the support has a towing point and the complete apparatus includes a tow line.
  • the support can be a harness for the user.
  • the device can include a propulsion motor and propeller mounted on a frame.
  • the user's support is then a seat on the frame, with the frame being normally provided with wheels and/or one or more floats for take off and landing.
  • the enclosure will be of a size such that its buoyancy is inadequate to lift the device and the user, without forward air speed to create extra lift for take off.
  • the canopy is preferably provided with means for spilling air from the canopy prior to its full deployment for lifting.
  • the means for spilling air can be a line for pulling down the edge of the canopy, normally on the windward edge, to spill air from its leeward edge, whereby the canopy collapses. Via a line held up by a pulley attached to the buoyancy, the windward edge can be lifted again for re-deployment.
  • the or at least some of the shroud lines are drawn radially inwards by a line passing over a pulley on the buoyancy.
  • the buoyant gas enclosure can be a toroidal bag arranged within the canopy towards its top. In this arrangement, air can be spilled from the edge of the canopy by drawing down the buoyant toroid, which releases tension in the shroud lines loosening the canopy edge for air spillage.
  • the bag could be positioned immediately on top of the canopy. Alternatively, the bag could be arranged above the canopy, attached to it by lines. It is envisaged that the enclosure will take other forms, such as a spherical bag above the canopy, or indeed a dirigible shape above the canopy.
  • the buoyant gas enclosure can be one or more of its cells which is closed to hold the gas. It is envisaged that all the cells could be closed to hold buoyant gas.
  • the means for spilling air from the parachute can comprises a pulley arrangement for drawing the two sides of the wing together until they are so configured as to no longer be able to provide aerodynamic lift from incident wind.
  • a pulley arrangement for drawing the two sides of the wing together until they are so configured as to no longer be able to provide aerodynamic lift from incident wind.
  • it way be provided with a central hinge.
  • it may have an anchor stay to the central hinge additional to the normal shroud lines.
  • the invention may be embodied in simple form as a parachute canopy to be incorporated by a third party with the existing equipment, such as a frame and propulsion motor.
  • a wing parachute canopy comprising a plurality of cells, each cell having:
  • the cells being closed at the trailing edge of the canopy; the canopy being characterised in that: • at least some of the cells are fully closed including at the front for inflation with gas and have
  • Each closed cell can have its own inflation gas inlet.
  • a plurality of closed cells can be inter-connected with a common inflation gas inlet.
  • a generally circular parachute canopy in combination with an inflatable enclosure arranged within the canopy when in use.
  • the enclosure can be a toroidal bag arranged within the canopy towards its top.
  • a generally circular parachute in combination with an inflatable enclosure arranged above the canopy when in use.
  • Figure 1 is side view of a flying device of the invention in use
  • Figure 2 is a similar view of the flying device of the invention moored prior to use
  • Figure 3 is a side view of a second flying device of the invention in use;
  • Figure 4 is a front view of the second flying device of the invention in use;
  • Figure 5 is a similar front view of the second flying device moored for use;
  • Figure 6 is a similar view to Figure 5 of a variant of the second flying device adapted for spillage of the air from its canopy;
  • Figure 7 is another front view of the Figure 6 variant showing canopy in a collapsed state
  • Figure 8 is a side view of a third flying device of the invention, shown with air being spilled from its canopy;
  • Figure 9 is a similar view to Figure 8 shown with the canopy being deployed;
  • Figure 10 is a similar view to Figure 8 of a variant.
  • the flying device thereshown comprises a parachute generally designated 1 and adapted as now described to be towed for lifting an aviator A.
  • the parachute has - as conventionally - a canopy 2, shroud lines 3 and harness 4.
  • the shroud lines are brought together at an upper part 5 of the harness, whilst a lower part 6 has a webbing seat 7 for supporting the weight of the aviator.
  • a tow point 8 is provided on the upper part of the harness, for a tow line 9 towing the device to give lift to the canopy for flying the aviator.
  • the canopy has a toroidal bag 11 attached midway up inside it. Its diameter is that of the canopy at the bag's position in the canopy.
  • the bag is filled via a valved inlet 12 such as a tyre valve with helium, rendering it buoyant.
  • a valved inlet 12 such as a tyre valve with helium, rendering it buoyant.
  • the canopy is held up even when not fully deployed by pressure of air through which it is travelling. This enables the aviator to step into the harness with the canopy off the ground and be launched without the canopy dragging on the ground.
  • the bag is sized such that its buoyancy is insufficient to lift the aviator.
  • additional shroud lines 21 are provided from the canopy at the points 22 of its attachment to the buoyant bag. These are brought down to an anchor point 23 in the form of a ring. It is connected to the harness by stays 24 to the regular shroud line connection points 25, two of these being provided one to either side of the towing point 8. When the anchor point is tethered, as by a releasable anchor line or hook 26, the stays are no longer in tension.
  • the shroud lines 3 are not in tension and the peripheral regions 27 of the canopy - outwards of the points 22 - are able to rise, spilling wind.
  • the anchor point 23 is held by the anchor line close to the ground, so that the rising of the peripheral regions does not lift the aviator.
  • the anchor point is released.
  • the canopy rises as a whole, including the buoyant tube, and the aviator takes off once he is being towed through the air sufficiently fast.
  • the aviator can reach the stays 24 to keep the peripheral regions from deploying before take-off, when the stays are slack with the anchor point held down but possibly released; the aviator is unlikely during normal flight to be able to reach and pull down on the stays 24 sufficiently to cause the peripheral regions to spill air and the device as a whole to lose buoyancy accidentally.
  • the flying device there shown comprises a wing parachute 101, having a double layer canopy 102, shroud lines 103 and a double pontoon float 104.
  • This latter has a seat 105 for an aviator A, engine 106 with a propeller 107.
  • Shroud points 108 are provided on lateral shroud frames 109.
  • the propeller drives the device forwards and the wing parachute lifts the float into the air. This is a known device.
  • certain 110 of the cells 111 between the upper skin 112, the lower skin 113 and side walls 114 are closed not only as is conventional at the rear 115, but also at the front 116. They are inflated via valved inlets 117 with helium, to hold the entire wing aloft prior to use.
  • the cell walls can be of polyurethane coated nylon fabric with taped joints.
  • the aviator is not constrained in manoeuvring to avoid collapse of the wing onto the water. If for instance he is travelling down wind at the speed of the wind, the air speed will not keep the wing deployed. However, its buoyant cells will. As shown in Figure 5, the float can be moored by line 118, with the wing aloft.
  • the wing parachute 201 attached to a float 204 has all its cells 211 closed for containing buoyant gas.
  • the canopy is divided into two sections 221,222. Each is provided with an inflation valve 217. Within each section, the cells are internally interconnected by apertures (not shown) in the cell side walls 214. Midway across the canopy, it has a discontinuity 220 in the cell structure, whereby the two sections 221,222 of the wing to either side can be hinged together. This is achieved by tightening an "air spillage" line 223 which leads up from the float to one edge of the wing. Here it passes over a pulley 224 and across to the other side of the wing.
  • the line 223 and pulley 224 is reproduced at the opposite side of the device in mirror image.
  • Figure 7 shows the line 223 fully tightened and the wing sections hinged against each other so that they can provide no aerodynamic lift. Most of the buoyancy of the wing is carried reacted in the line 223.
  • several similarly rigged lines will be provided, to spread the reaction evenly between the wing sections and fore & aft within the wing.
  • Some of the reaction will be taken by additional anchor line(s) 224 passing from the float to the hinge.
  • the additional anchor lines control the overall rise of the canopy as the spillage line(s) are released for the next flight. With the hinge restrained, the wing sections spread evenly. Once the wing is deployed, the spillage and anchor lines are fully released to allow the shrouds to connect the float and the canopy in the normal way.
  • Figure 8 shows an alternative arrangement of a generally circular canopy parachute 301 similar to that of Figures 1 & 2, except that the toroidal buoyant bag 11 is replaced big a dirigible shaped bag 311 arranged above the canopy.
  • the canopy has the usual shroud lines 303, including a main buoyancy line 331, which is attached to the centre of the canopy.
  • the relative length of the shroud lines and the point of attachment 332 of the centre of the canopy is such as to give it the usual depressed dome.
  • the main buoyancy line continues up to the bag 311.
  • An air spill line 333 is connected to a point 334 on the edge of the canopy, which is upwind when the device is not in use.
  • One end of the air spill line 333 extends down to the harness, where it is in effect an additional shroud line in flight.
  • the other passes up outside the canopy around a pulley 335, fastened immediately below the buoyancy bag, and down 336 to the harness. It performs no function in flight.
  • connection point 334 On landing, the aviator, or a helper on the ground grasps the air spill line and carries it upwind. Normally the connection point 334 will be on the front edge of the canopy and the aviator will have landed into the wind. However, if not, hauling H the air spill line upwind W will turn the canopy. As the connection point is hauled down D, the canopy will collapse, with the wind on its outer surface. The rest of the canopy will be in the lee. Air will spill S from it and it will also collapse C. With the top of the canopy still held aloft, the canopy will remain collapsed, at least in the strength of wind for which the device is designed.
  • the harness may be anchored A.
  • FIG. 10 this variant of the Figure 8 embodiment has a different arrangement for spilling air from the canopy on landing.
  • a set of rings 440 is a attached by a set radial cords 441 to an air spill line 433, which passes up over pulley 435 at the buoyant bag 411 and down to another pulley 437 at the harness.
  • the other end 436 is also taken down to the pulley 437.
  • the rings 440 are loose on selected ones of the shroud lines 403.
  • the aviator pulls on the air spill line 433.
  • the radial cords 441 are of limited length, the shroud lines having the rings on them are drawn in. This effectively causes collapse C of the canopy, or at least substantial restriction of its developed area.
  • the canopy is kept collapsed, though supported by the buoyant bag, by anchoring of the air spill line.
  • air spill line is released and the deployment line 436 is pulled down. This, and the weight of the rings, releases the gathering together of shroud lines.
  • the canopy is now able to deploy in the wind and/or the towing movement through the air.
  • the shroud lines Apart from the obvious advantage in holding the canopy aloft, but collapsed, in that it is not wetted nor damaged, the shroud lines also are held up - albeit not taut - and hence not prone to entanglement.
  • the canopy of any of the above embodiments can be hauled done by hand with the shroud lines, bearing in mind that the buoyancy of the inflated cells is insufficient to lift the user.
  • the valves 12, 117, 217 are released and the helium allowed to escape. The canopy can then be stowed.
  • the float may be a land vehicle with wheels. Indeed the float itself may be equipped with wheels to make it amphibious.
  • a small float tube may be provided. The aviator sits in this until lifted from it by the parachute. So that the float is not lost, it can be secured by a line to the main tow line or to the aviator's harness. It hangs down in flight.
  • Figure 1 devices possibly with the floats just described, can be coupled together for flying one behind the other, so that several people can fly together, one below each parachute.
  • one or more additional parachutes may be rigged above the first, in a bi- or tri-plane configuration.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Toys (AREA)

Abstract

L'invention concerne un dispositif volant composé d'un parachute de type aile (101), comprenant une voilure à double couche (102), des suspentes (103), un ponton flottant double (104) comprenant un siège (105) destiné à un aviateur A et un moteur (106) muni d'un hélice (107). Les anneaux des suspentes (108) sont situés sur des structures latérales de suspentes (109). Certains (110) des caissons (111) situés entre la peau supérieure (112) et la peau inférieure (113) et les parois latérales (114) sont fermés, pas uniquement à l'arrière (115) comme dans les parachutes classiques, mais également à l'avant (116). Ces caissons sont gonflés par l'intermédiaire d'entrées à valve (117) à l'aide d'hélium, afin de maintenir l'aile en l'air avant son utilisation. Ainsi, le flotteur peut être lancé et le parachute déployé sans qu'il ait de risque de voir retomber l'aile dans l'eau.
PCT/US2001/008391 2000-03-20 2001-03-16 Parachute avec caissons gonflables Ceased WO2001070571A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU2001247470A AU2001247470A1 (en) 2000-03-20 2001-03-16 Parachute with inflatable enclosure

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US19065300P 2000-03-20 2000-03-20
US60/190,653 2000-03-20

Publications (1)

Publication Number Publication Date
WO2001070571A1 true WO2001070571A1 (fr) 2001-09-27

Family

ID=22702221

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2001/008391 Ceased WO2001070571A1 (fr) 2000-03-20 2001-03-16 Parachute avec caissons gonflables

Country Status (2)

Country Link
AU (1) AU2001247470A1 (fr)
WO (1) WO2001070571A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106741969A (zh) * 2016-12-30 2017-05-31 深圳市筋斗云技术有限公司 一种主动膨胀快速展开降落伞的装置和方法
CN109250123A (zh) * 2018-10-19 2019-01-22 航宇救生装备有限公司 一种开缝式充气冲压翼伞
CN109398695A (zh) * 2018-12-13 2019-03-01 安徽科技学院 一种安装角可调的前缘气室自动成形冲压翼伞

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1777685A (en) * 1929-01-31 1930-10-07 Warner Frederick Douglas Parachute deflater
US4105173A (en) * 1973-11-26 1978-08-08 Bucker Henrique Oswaldo Inflatable parachute for use as escape or sporting device
EP0411222A1 (fr) * 1989-07-31 1991-02-06 Ing-Lang Tsay Parachute pneumatique multicouche
FR2685284A1 (fr) * 1991-12-19 1993-06-25 Lehn Pierre Dispositif de loisir sportif aerien.
US5620153A (en) * 1995-03-20 1997-04-15 Ginsberg; Harold M. Light aircraft with inflatable parachute wing propelled by a ducted propeller

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1777685A (en) * 1929-01-31 1930-10-07 Warner Frederick Douglas Parachute deflater
US4105173A (en) * 1973-11-26 1978-08-08 Bucker Henrique Oswaldo Inflatable parachute for use as escape or sporting device
EP0411222A1 (fr) * 1989-07-31 1991-02-06 Ing-Lang Tsay Parachute pneumatique multicouche
FR2685284A1 (fr) * 1991-12-19 1993-06-25 Lehn Pierre Dispositif de loisir sportif aerien.
US5620153A (en) * 1995-03-20 1997-04-15 Ginsberg; Harold M. Light aircraft with inflatable parachute wing propelled by a ducted propeller

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106741969A (zh) * 2016-12-30 2017-05-31 深圳市筋斗云技术有限公司 一种主动膨胀快速展开降落伞的装置和方法
CN109250123A (zh) * 2018-10-19 2019-01-22 航宇救生装备有限公司 一种开缝式充气冲压翼伞
CN109398695A (zh) * 2018-12-13 2019-03-01 安徽科技学院 一种安装角可调的前缘气室自动成形冲压翼伞

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Publication number Publication date
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