US20020092952A1 - Parachutes - Google Patents

Parachutes Download PDF

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Publication number
US20020092952A1
US20020092952A1 US10/013,834 US1383401A US2002092952A1 US 20020092952 A1 US20020092952 A1 US 20020092952A1 US 1383401 A US1383401 A US 1383401A US 2002092952 A1 US2002092952 A1 US 2002092952A1
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US
United States
Prior art keywords
canopy
lines
skirt
skirt assist
line
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.)
Abandoned
Application number
US10/013,834
Inventor
Nigel Parker
David Hirst
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.)
Wardle Storeys Safety and Survival Equipment Ltd
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
Assigned to WARDLE STOREYS (SAFETY & SURVIVAL EQUIPMENT) LIMITED reassignment WARDLE STOREYS (SAFETY & SURVIVAL EQUIPMENT) LIMITED ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: HIRST, DAVID RICHARD JORDAN, PARKER, NIGEL STUART
Publication of US20020092952A1 publication Critical patent/US20020092952A1/en
Priority to US10/406,005 priority Critical patent/US6769650B2/en
Abandoned legal-status Critical Current

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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
    • B64D17/22—Load suspension
    • B64D17/36—Load suspension incorporating friction devices or frangible connections to reduce shock loading of canopy
    • 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

Definitions

  • the invention relates to parachutes.
  • the term “parachutes” is intended to cover any type of parachute provided with a canopy with rigging lines connecting the canopy to a load. When such a parachute is deployed, air enters the canopy of the parachute and inflates the canopy. When the canopy is deployed at low speeds and at low levels, the inflation may not be sufficiently rapid to ensure satisfactory opening.
  • skirt assist lines It is a problem with such skirt assist lines that, at higher speeds, the rapid deployment of the portion of the canopy between the connection points of the skirt assist lines and the lower edge of the canopy can induce g-forces on a load which are undesirable.
  • the load may be a parachutist or cargo. This is particularly true where the load is a person and can occur, for example, where the parachute forms part of an ejection seat which may be deployed at high or low levels and at high or low speeds.
  • a parachute comprising a canopy having a lower edge, rigging lines connecting the canopy to a load, and a plurality of skirt assist lines, each skirt assist line extending between a respective rigging line and a respective point on the interior of the canopy such that a portion of the canopy between the point and the lower edge is relieved of tension as the canopy is deployed to assist the opening of the canopy, the skirt assist lines being frangible.
  • skirt assist lines By making the skirt assist lines frangible, the skirt assist lines can be rendered inoperative in circumstances where their operation would cause undesirable g-forces.
  • FIG. 1 is a schematic view of a parachute showing a canopy of the parachute in a first stage of deployment and rigging lines for connection to a load with skirt assist lines extending between the rigging lines and the canopy,
  • FIG. 2 is a similar view to FIG. 1 but showing the skirt assist lines broken.
  • the parachute comprises a canopy indicated diagrammatically at 10 by rigging lines, some of which are shown at 11 , attached to a parachutist or cargo shown schematically at 18 .
  • the canopy 10 has a lower edge 12 and an apex 13 and may be of any suitable construction. In general, the canopy will be formed by gores (not shown) interconnected by seams.
  • the canopy 10 may be of any known shape and be for any intended purpose.
  • the canopy may be generally conical and may be deployed by static line or used in free fall.
  • the canopy may be provided as part of an aircraft ejection seat.
  • the parachute is provided with skirt assist lines 15 .
  • Each skirt assist line 15 is connected between a rigging line 11 and the canopy 10 .
  • the connection is between a point 16 on the rigging line 11 adjacent the lower edge 12 of the canopy and a point 17 on the interior of the canopy 10 spaced from the lower edge 12 .
  • the length of each skirt assist line 15 is less than the distance between the points 16 , 17 along the associated rigging line 11 and along the canopy 10 .
  • the connection point 17 on the canopy will be along a main seam between two adjacent gores of the canopy 10 .
  • the canopy 10 and the rigging lines 11 are packed in a deployment bag or container (not shown) from which the canopy 10 is deployed. As indicated above, this deployment may be manual or automatic. On deployment, the canopy 10 streams from the deployment bag or container and adopts the uninflated disposition shown in FIG. 1.
  • the effect of the skirt assist lines 15 is to relieve from tension the portion of the canopy 10 between the lower edge 12 and the points 17 of connection of the skirt assist lines 15 on the canopy 10 . This allows this portion of the canopy 10 to move outwardly rapidly in the air flow to promote fast inflation of the canopy. This is particularly advantageous when deployment is at low level and/or low speed.
  • the skirt assist lines 15 are frangible. The purpose of this is to prevent the portion of the canopy 10 between the lower edge 12 and the points 17 of connection of the skirt assist lines 15 on the canopy 10 from moving outwardly on deployment of the canopy 10 . This is desirable when the canopy 10 is deployed at high speeds in order to prevent the parachutist or other load 18 , being subjected to undesirably high g-forces. Under such circumstances, the higher speed of deployment is sufficient to ensure satisfactory inflation of the canopy 10 .
  • the skirt assist lines 15 may be made frangible and or severable in a number of ways and at any point.
  • each skirt assist line 15 may be provided with a weak point designed to break under a predetermined load equivalent to that experienced by the rigging line 11 when the canopy 10 opens at high speed. Accordingly, on such high speed opening of the canopy 10 , the skirt assist lines 15 break at the weak points to prevent rapid outward opening of the portion of the canopy 10 between the lower edge 12 and the points 17 of connection of the skirt assist lines 15 on the canopy 10 . The g-forces on the load are thus reduced.
  • each skirt assist line 15 may be provided with a device that severs the skirt assist line 15 when high speed opening loads are sensed. This achieves the same effect as the weak points.
  • the skirt assist lines 15 may be able to be broken prior to deployment of the canopy 10 .
  • the skirt assist lines 15 may be severable at any time before deployment.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Air Bags (AREA)
  • Toys (AREA)
  • Emergency Lowering Means (AREA)

Abstract

A parachute has a canopy and rigging lines with skirt assist lines connected between a point on each rigging line adjacent a lower edge of the canopy and a point on the interior of the canopy spaced from the lower edge. The arrangement is such that a portion of the canopy between the point and the lower edge is relieved of tension as the canopy is deployed to assist the opening of the canopy. The skirt assist lines are frangible. This prevents rapid deployment of the canopy to lower g-forces on the load in high speed opening.

Description

    BACKGROUND TO THE INVENTION
  • 1. Field of the Invention [0001]
  • The invention relates to parachutes. [0002]
  • 2. Brief Review of the Prior Art [0003]
  • The term “parachutes” is intended to cover any type of parachute provided with a canopy with rigging lines connecting the canopy to a load. When such a parachute is deployed, air enters the canopy of the parachute and inflates the canopy. When the canopy is deployed at low speeds and at low levels, the inflation may not be sufficiently rapid to ensure satisfactory opening. In order to improve the opening, it is known to provide a plurality of skirt assist lines. Each skirt assist line extends between a respective rigging line and a respective point on the interior of the canopy such that a portion of the canopy between the point and the lower edge of the canopy is relieved of tension as the canopy is deployed. As a result, this portion of the canopy spreads very rapidly and assists in rapid opening of the remainder of the canopy. [0004]
  • It is a problem with such skirt assist lines that, at higher speeds, the rapid deployment of the portion of the canopy between the connection points of the skirt assist lines and the lower edge of the canopy can induce g-forces on a load which are undesirable. The load may be a parachutist or cargo. This is particularly true where the load is a person and can occur, for example, where the parachute forms part of an ejection seat which may be deployed at high or low levels and at high or low speeds. [0005]
    • SUMMARY OF THE INVENTION
  • According to the invention, there is provided a parachute comprising a canopy having a lower edge, rigging lines connecting the canopy to a load, and a plurality of skirt assist lines, each skirt assist line extending between a respective rigging line and a respective point on the interior of the canopy such that a portion of the canopy between the point and the lower edge is relieved of tension as the canopy is deployed to assist the opening of the canopy, the skirt assist lines being frangible. [0006]
  • By making the skirt assist lines frangible, the skirt assist lines can be rendered inoperative in circumstances where their operation would cause undesirable g-forces. [0007]
  • The following is a more detailed description of an embodiment of the invention, by way of example, reference being made to the accompanying drawings in which:[0008]
    • BRIEF DESCRIPTION OF THE DRAWINGS
  • FIG. 1 is a schematic view of a parachute showing a canopy of the parachute in a first stage of deployment and rigging lines for connection to a load with skirt assist lines extending between the rigging lines and the canopy, [0009]
  • FIG. 2 is a similar view to FIG. 1 but showing the skirt assist lines broken. [0010]
    • DESCRIPTION OF THE PREFERRED EMBODIMENTS
  • Referring first to FIG. 1, the parachute comprises a canopy indicated diagrammatically at [0011] 10 by rigging lines, some of which are shown at 11, attached to a parachutist or cargo shown schematically at 18. The canopy 10 has a lower edge 12 and an apex 13 and may be of any suitable construction. In general, the canopy will be formed by gores (not shown) interconnected by seams.
  • The [0012] canopy 10 may be of any known shape and be for any intended purpose. For example, the canopy may be generally conical and may be deployed by static line or used in free fall. The canopy may be provided as part of an aircraft ejection seat.
  • The parachute is provided with [0013] skirt assist lines 15. Each skirt assist line 15 is connected between a rigging line 11 and the canopy 10. The connection is between a point 16 on the rigging line 11 adjacent the lower edge 12 of the canopy and a point 17 on the interior of the canopy 10 spaced from the lower edge 12. The length of each skirt assist line 15 is less than the distance between the points 16,17 along the associated rigging line 11 and along the canopy 10. In general, the connection point 17 on the canopy will be along a main seam between two adjacent gores of the canopy 10. There may be a skirt assist line 15 between every rigging line 11 and the canopy 10 or only between some rigging lines 11 and the canopy.
  • In use, the [0014] canopy 10 and the rigging lines 11 are packed in a deployment bag or container (not shown) from which the canopy 10 is deployed. As indicated above, this deployment may be manual or automatic. On deployment, the canopy 10 streams from the deployment bag or container and adopts the uninflated disposition shown in FIG. 1. The effect of the skirt assist lines 15 is to relieve from tension the portion of the canopy 10 between the lower edge 12 and the points 17 of connection of the skirt assist lines 15 on the canopy 10. This allows this portion of the canopy 10 to move outwardly rapidly in the air flow to promote fast inflation of the canopy. This is particularly advantageous when deployment is at low level and/or low speed.
  • The [0015] skirt assist lines 15 are frangible. The purpose of this is to prevent the portion of the canopy 10 between the lower edge 12 and the points 17 of connection of the skirt assist lines 15 on the canopy 10 from moving outwardly on deployment of the canopy 10. This is desirable when the canopy 10 is deployed at high speeds in order to prevent the parachutist or other load 18, being subjected to undesirably high g-forces. Under such circumstances, the higher speed of deployment is sufficient to ensure satisfactory inflation of the canopy 10.
  • The [0016] skirt assist lines 15 may be made frangible and or severable in a number of ways and at any point.
  • First, each [0017] skirt assist line 15 may be provided with a weak point designed to break under a predetermined load equivalent to that experienced by the rigging line 11 when the canopy 10 opens at high speed. Accordingly, on such high speed opening of the canopy 10, the skirt assist lines 15 break at the weak points to prevent rapid outward opening of the portion of the canopy 10 between the lower edge 12 and the points 17 of connection of the skirt assist lines 15 on the canopy 10. The g-forces on the load are thus reduced.
  • As an alternative to weak points, each [0018] skirt assist line 15 may be provided with a device that severs the skirt assist line 15 when high speed opening loads are sensed. This achieves the same effect as the weak points.
  • Additionally or alternatively, the [0019] skirt assist lines 15 may be able to be broken prior to deployment of the canopy 10. For example, the skirt assist lines 15 may be severable at any time before deployment.

Claims (6)

We claim:
1. A parachute comprising a canopy having a lower edge, rigging lines connecting the canopy to a load and a plurality of skirt assist lines, each skirt assist line extending between a respective rigging line and a respective point on the interior of the canopy such that a portion of the canopy between the point and the lower edge is relieved of tension as the canopy is deployed to assist the opening of the canopy, the skirt assist lines being frangible.
2. A parachute according to claim 1 wherein the skirt assist lines are frangible prior to deployment of the canopy.
3. A parachute according to claim 1 wherein the skirt assist lines are frangible during deployment of the canopy if the load in the skirt assist lines exceed a predetermined maximum.
4. A parachute according to claim 3 wherein each skirt assist line includes a weak point designed to break the associated skirt assist line if the load in the skirt assist line exceeds a predetermined maximum.
5. A parachute according to claim 2 wherein each skirt assist line is severable.
6. A parachute according to claim 5 wherein means are associated with each skirt assist line for severing the skirt assist line.
US10/013,834 2000-12-13 2001-12-13 Parachutes Abandoned US20020092952A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US10/406,005 US6769650B2 (en) 2000-12-13 2003-04-03 Parachutes

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB0030396.6 2000-12-13
GB0030396A GB2370022B (en) 2000-12-13 2000-12-13 Parachutes

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US10/406,005 Continuation US6769650B2 (en) 2000-12-13 2003-04-03 Parachutes

Publications (1)

Publication Number Publication Date
US20020092952A1 true US20020092952A1 (en) 2002-07-18

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Family Applications (2)

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US10/013,834 Abandoned US20020092952A1 (en) 2000-12-13 2001-12-13 Parachutes
US10/406,005 Expired - Lifetime US6769650B2 (en) 2000-12-13 2003-04-03 Parachutes

Family Applications After (1)

Application Number Title Priority Date Filing Date
US10/406,005 Expired - Lifetime US6769650B2 (en) 2000-12-13 2003-04-03 Parachutes

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US (2) US20020092952A1 (en)
EP (1) EP1215116B8 (en)
DE (1) DE60111168T2 (en)
ES (1) ES2239653T3 (en)
GB (1) GB2370022B (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20080029649A1 (en) * 2005-09-21 2008-02-07 Sadeck James E Continuous disreefing apparatus for parachute

Family Cites Families (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB266345A (en) * 1926-02-17 1927-07-14 Herbert Ray Mcclintock Improvements in or relating to parachutes
US1872705A (en) * 1930-04-26 1932-08-23 Benjamin L Elliott Parachute
GB531680A (en) * 1939-02-28 1941-01-09 Helmut Michel Improvements in and relating to parachutes
GB552895A (en) * 1941-09-26 1943-04-29 John Raymond Cuthbert Quilter Improvements in or relating to parachutes
US2523276A (en) * 1947-09-25 1950-09-26 Walter C Buhler Airfoil parachute
GB776296A (en) * 1954-10-12 1957-06-05 English Electric Co Ltd Improvements in and relating to parachute release or disreefing devices
US3110459A (en) * 1961-08-29 1963-11-12 Helmut G Heinrich Parachute
US3385539A (en) * 1966-08-05 1968-05-28 Northrop Corp Parachute assembly for aerial recovery
US3420478A (en) * 1967-04-26 1969-01-07 Recovery Systems Research Inc Parachute
US3586269A (en) * 1969-09-15 1971-06-22 Stencel Aero Eng Corp Means for reefing a pilot parachute
GB2102357B (en) * 1981-07-28 1985-02-27 Secr Defence Parachutes - reducing shock loading
DE3236533A1 (en) * 1982-10-02 1984-04-05 Peter 7987 Weingarten Kostelezky PARACHUTE
GB2220626A (en) * 1988-06-28 1990-01-17 Irvin Great Britain Ltd Parachutes
US4955563A (en) * 1989-08-25 1990-09-11 The United States Of America As Represented By The Secretary Of The Army Apparatus and method for controlled simultaneous opening of clustered parachutes
US5248117A (en) * 1992-04-08 1993-09-28 The United States Of America As Represented By The Secretary Of The Navy Regulated drag area parachute
US5388787A (en) * 1993-11-23 1995-02-14 Irvin Industries Canada Ltd. Air impermeable parachute canopy with opening assist
GB2322606B (en) * 1997-03-01 2001-04-11 Wardle Storeys Ltd Parachutes
US5893536A (en) * 1998-05-28 1999-04-13 The United States Of America As Represented By The Secretary Of The Army Parafoil assembly

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20080029649A1 (en) * 2005-09-21 2008-02-07 Sadeck James E Continuous disreefing apparatus for parachute
US7416158B2 (en) 2005-09-21 2008-08-26 The United States Of America As Represented By The Secretary Of The Army Continuous disreefing apparatus for parachute

Also Published As

Publication number Publication date
ES2239653T3 (en) 2005-10-01
EP1215116B8 (en) 2005-07-27
GB0030396D0 (en) 2001-01-24
GB2370022A (en) 2002-06-19
US20040065782A1 (en) 2004-04-08
EP1215116B1 (en) 2005-06-01
EP1215116A2 (en) 2002-06-19
GB2370022B (en) 2004-12-22
US6769650B2 (en) 2004-08-03
DE60111168T2 (en) 2005-11-10
EP1215116A3 (en) 2002-09-25
DE60111168D1 (en) 2005-07-07

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Legal Events

Date Code Title Description
AS Assignment

Owner name: WARDLE STOREYS (SAFETY & SURVIVAL EQUIPMENT) LIMIT

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:PARKER, NIGEL STUART;HIRST, DAVID RICHARD JORDAN;REEL/FRAME:012674/0336

Effective date: 20020110

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION