WO2002076828A1 - Parachute retardation device - Google Patents

Parachute retardation device Download PDF

Info

Publication number
WO2002076828A1
WO2002076828A1 PCT/ZA2002/000036 ZA0200036W WO02076828A1 WO 2002076828 A1 WO2002076828 A1 WO 2002076828A1 ZA 0200036 W ZA0200036 W ZA 0200036W WO 02076828 A1 WO02076828 A1 WO 02076828A1
Authority
WO
WIPO (PCT)
Prior art keywords
parachute
retardation
retardation device
load
retraction
Prior art date
Application number
PCT/ZA2002/000036
Other languages
French (fr)
Inventor
Deon Labuschagne
Original Assignee
Aerosud (Pty) Ltd
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 Aerosud (Pty) Ltd filed Critical Aerosud (Pty) Ltd
Publication of WO2002076828A1 publication Critical patent/WO2002076828A1/en

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D17/00—Parachutes
    • B64D17/22—Load suspension
    • B64D17/24—Rigging lines
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D17/00—Parachutes
    • B64D17/78—Parachutes in association with other load-retarding apparatus

Definitions

  • This invention relates to a parachute retardation device.
  • USA patent number 6,050,524 discloses a device for reducing the impact velocity of a parachutist by a length-shortening retraction device.
  • the retraction device is operated by a gas generator, which is activated by a ground proximity sensor.
  • the retraction device is mounted between the load and the conventional suspension lines and a disadvantage of the known device is that a substantial force has to be applied to shorten the suspension lines. High stress forces are thus generated in the suspension lines and the device is not suitable for use with heavy loads.
  • a parachute retardation device for retarding the downward velocity of a load carried by a parachute, the retardation device comprising increasing means for increasing the effective surface of the parachute.
  • the increasing means includes: a retraction device connectable to the load for moving the load and the parachute towards each other; and - connecting means for connecting the retraction device to the parachute, the connecting means comprising a plurality of elongate members, a first end of each member being connected to the retraction device and a second end of each elongate member being connected to a region of the parachute towards but inwards from the periphery of the parachute.
  • the parachute retardation device may further include a sensing means for sensing the approach of the load to the ground.
  • the parachute retardation device may even further include an activating mechanism for activating the retraction device in response to a signal received from the sensing means.
  • the first ends of the elongate members may be connected to each other.
  • the elongate members may be in the form of a plurality of secondary cables and the first ends of the secondary cables may further be connected to the retraction device by a primary cable.
  • the parachute may be in the shape of a dome and for optimum performance, the second end of each secondary cable may be connected to the dome- shaped parachute in the region of the outer middle annular quarter of the dome.
  • the retraction device may be in the form of a servo-mechanism including a piston and cylinder assembly and two sets of pulleys, each set being connected to either the piston or the cylinder.
  • the primary cable may be suspended over the pulleys, with the operatively lower end of the primary cable being connected to either the piston or the cylinder.
  • the retraction device may further include a gas expansion device disposed inside the cylinder to be activated by the activating mechanism, for moving the piston outwardly relative to the cylinder, to expand the retraction device and thus to draw in the primary cable.
  • a parachute having a retardation device according to the first aspect of the invention.
  • figure 1 is a longitudinal-sectional side view of a parachute provided with a retardation device according to a preferred embodiment of the invention in a pre-retarded condition
  • figure 2 is the same view as that of figure 1 , with the retardation device in a retarded condition
  • figure 3 is a longitudinal-sectional side view of the retardation device of figure 1
  • figure 4 is a top view of the parachute of figure 1.
  • a parachute 10 according to a preferred embodiment of the invention is provided with a retardation device 12 (shown in more detail in figure 3).
  • the retardation device 12 is particularly suitable for retarding the downward velocity of a load 14 carried by the parachute 10.
  • the retardation device 12 includes an increasing means for increasing the effective surface of the parachute 10, comprising a retraction device 12.5 connectable to the load 14 for moving the load 14 and the parachute 10 towards each other.
  • the increasing means further includes connecting means for connecting the retraction device 12.5 to the parachute 10.
  • the connecting means comprises a primary cable 18 and a set of between eight and fourteen, preferably twelve secondary cables 20. A first or lower end of each secondary cable 20 is connected to the retraction device 12.5 via the primary cable 18, and a second or upper end of each is connected to a region R of the parachute 10 towards but inwards from the periphery of the parachute 10.
  • the parachute 10 is dome shaped and could be divided into annular quarters by imaginary lines depicted in figure 4 comprising a middle quarter 23, inner middle quarter 24, outer middle quarter 25 and a peripheral quarter 26.
  • the region R is the outer middle annular quarter 25 of the dome shaped parachute 10.
  • the retardation device 12 further includes a proximity sensor 22 for sensing the approach and close proximity of the load 14 to the ground.
  • the retraction device 12.5 is in the form of a servo- mechanism including a piston and cylinder assembly 12.1 and 12.2 respectively, and two sets of pulleys 12.3.
  • One set of pulleys 12.3 is mounted on the outside end of the cylinder 12.2 and the other set of pulleys is mounted on the rod of the piston 12.1.
  • the primary cable 18 is suspended over the pulleys 12.3, with the operatively lower end of the primary cable 18 being connected to the rod of the piston 12.1.
  • the retardation device 12 even further includes an activating mechanism for activating the retraction device 12.5 in response to a signal received from the sensor 22.
  • the activating mechanism comprises a gas expansion device 12.4 disposed inside the cylinder 12.2 and which is activated by a signal from the sensor 22, to move the piston 12.1 outwardly relative to the cylinder 12.2 as indicated by arrows A and B in figure 3, to expand the retraction device 12.5 and thus to draw in the primary cable 18.
  • the primary cable 18 pulls the secondary cables 20 in the direction of arrows C in figure 1, which causes the air inside the parachute to accelerate and the portion of the parachute towards but inwardly from the periphery of the parachute 10 is pulled downwards by the secondary cables 20, to increase the effective surface of the parachute 10.

Abstract

This invention provides a parachute (10) provided with a retardation device (12), for retarding the downward velocity of a load (14) carried by the parachute (10). The retardation device (12) includes means for increasing the effective surface of the parachute (10), comprising a retraction device (12.5) connectable to the load (14) for moving the load (14) and the parachute (10) towards each other. The retraction device (12.5) is connected to the parachute (10) by a primary cable (18) and a set of secondary cables (20). A lower end of each secondary cable (20) is connected to the retraction device (12.5) via the primary cable (18). An upper end of each secondary cable is connected to an outer middle annular quarter region R of the parachute (10). The retardation device (12) further includes a proximity sensor (22) for sensing the approach and close proximity of the load (14) to the ground.

Description

PARACHUTE RETARDATION DEVICE
INTRODUCTION AND BACKGROUND TO THE INVENTION
This invention relates to a parachute retardation device.
A number of parachute retardation or shock absorption devices are known, for example those disclosed in USA patents 4,127,246; 4,333,621 ; and 6,050,524. USA patent number 6,050,524 discloses a device for reducing the impact velocity of a parachutist by a length-shortening retraction device. The retraction device is operated by a gas generator, which is activated by a ground proximity sensor.
The retraction device is mounted between the load and the conventional suspension lines and a disadvantage of the known device is that a substantial force has to be applied to shorten the suspension lines. High stress forces are thus generated in the suspension lines and the device is not suitable for use with heavy loads.
OBJECT OF THE INVENTION It is therefore an object of the present invention to provide a parachute retardation device with which the aforesaid disadvantage can be overcome or at least minimised. SUMMARY OF THE INVENTION
According to a first aspect of the invention there is provided a parachute retardation device for retarding the downward velocity of a load carried by a parachute, the retardation device comprising increasing means for increasing the effective surface of the parachute.
Further according to the invention the increasing means includes: a retraction device connectable to the load for moving the load and the parachute towards each other; and - connecting means for connecting the retraction device to the parachute, the connecting means comprising a plurality of elongate members, a first end of each member being connected to the retraction device and a second end of each elongate member being connected to a region of the parachute towards but inwards from the periphery of the parachute.
The parachute retardation device may further include a sensing means for sensing the approach of the load to the ground.
The parachute retardation device may even further include an activating mechanism for activating the retraction device in response to a signal received from the sensing means.
The first ends of the elongate members may be connected to each other. The elongate members may be in the form of a plurality of secondary cables and the first ends of the secondary cables may further be connected to the retraction device by a primary cable.
The parachute may be in the shape of a dome and for optimum performance, the second end of each secondary cable may be connected to the dome- shaped parachute in the region of the outer middle annular quarter of the dome.
The retraction device may be in the form of a servo-mechanism including a piston and cylinder assembly and two sets of pulleys, each set being connected to either the piston or the cylinder. The primary cable may be suspended over the pulleys, with the operatively lower end of the primary cable being connected to either the piston or the cylinder.
The retraction device may further include a gas expansion device disposed inside the cylinder to be activated by the activating mechanism, for moving the piston outwardly relative to the cylinder, to expand the retraction device and thus to draw in the primary cable.
According to a second aspect of the invention there is provided a parachute having a retardation device according to the first aspect of the invention. BRIEF DESCRIPTION OF THE DRAWINGS
The invention will now be described further by way of a non-limiting example with reference to the accompanying drawings wherein: figure 1 is a longitudinal-sectional side view of a parachute provided with a retardation device according to a preferred embodiment of the invention in a pre-retarded condition; figure 2 is the same view as that of figure 1 , with the retardation device in a retarded condition; figure 3 is a longitudinal-sectional side view of the retardation device of figure 1 ; and figure 4 is a top view of the parachute of figure 1.
DESCRIPTION OF A PREFERRED EMBODIMENT OF THE INVENTION
Referring to figures 1 and 2, a parachute 10 according to a preferred embodiment of the invention is provided with a retardation device 12 (shown in more detail in figure 3). The retardation device 12 is particularly suitable for retarding the downward velocity of a load 14 carried by the parachute 10.
The retardation device 12 includes an increasing means for increasing the effective surface of the parachute 10, comprising a retraction device 12.5 connectable to the load 14 for moving the load 14 and the parachute 10 towards each other. The increasing means further includes connecting means for connecting the retraction device 12.5 to the parachute 10. The connecting means comprises a primary cable 18 and a set of between eight and fourteen, preferably twelve secondary cables 20. A first or lower end of each secondary cable 20 is connected to the retraction device 12.5 via the primary cable 18, and a second or upper end of each is connected to a region R of the parachute 10 towards but inwards from the periphery of the parachute 10.
The parachute 10 is dome shaped and could be divided into annular quarters by imaginary lines depicted in figure 4 comprising a middle quarter 23, inner middle quarter 24, outer middle quarter 25 and a peripheral quarter 26. The region R is the outer middle annular quarter 25 of the dome shaped parachute 10.
The retardation device 12 further includes a proximity sensor 22 for sensing the approach and close proximity of the load 14 to the ground.
Referring to figure 3, the retraction device 12.5 is in the form of a servo- mechanism including a piston and cylinder assembly 12.1 and 12.2 respectively, and two sets of pulleys 12.3. One set of pulleys 12.3 is mounted on the outside end of the cylinder 12.2 and the other set of pulleys is mounted on the rod of the piston 12.1.
The primary cable 18 is suspended over the pulleys 12.3, with the operatively lower end of the primary cable 18 being connected to the rod of the piston 12.1. The retardation device 12 even further includes an activating mechanism for activating the retraction device 12.5 in response to a signal received from the sensor 22. The activating mechanism comprises a gas expansion device 12.4 disposed inside the cylinder 12.2 and which is activated by a signal from the sensor 22, to move the piston 12.1 outwardly relative to the cylinder 12.2 as indicated by arrows A and B in figure 3, to expand the retraction device 12.5 and thus to draw in the primary cable 18. The primary cable 18 pulls the secondary cables 20 in the direction of arrows C in figure 1, which causes the air inside the parachute to accelerate and the portion of the parachute towards but inwardly from the periphery of the parachute 10 is pulled downwards by the secondary cables 20, to increase the effective surface of the parachute 10.
The downward speed of the load 14 is thus retarded just before it hits the ground.
It will be appreciated that variations in detail are possible with a parachute retardation device according to the invention without departing from the scope of the appended claims.

Claims

1. A parachute retardation device for retarding the downward velocity of a load carried by a parachute, the retardation device comprises increasing means for increasing the effective surface of the parachute.
2. A parachute retardation device according to claim 1 , wherein the increasing means includes a retraction device connectable to the load for moving the load and the parachute towards each other; and connecting means for connecting the retraction device to the parachute.
3. A parachute retardation device according to claim 2 wherein the connecting means comprises a plurality of elongate members, a first end of each member being connected to the retraction device and a second end of each member being connected to a region of the parachute towards but inwards from the periphery of the parachute.
4. A parachute retardation device according to claim 3 wherein the first ends of the elongate members are connected to each other.
5. A parachute retardation device according to claim 3 or 4 wherein the elongate members are in the form of a plurality of secondary cables and the first ends of the secondary cables are further connected to the retraction device by a primary cable.
6. A parachute retardation device according to claim 5 wherein the parachute is dome-shaped and wherein the second end of each secondary cable is connected to the dome-shaped parachute in the region of the outer middle annular quarter of the dome.
7. A parachute retardation device according to any one of claims 2 to 6, which includes a sensing means for sensing the approach of the load to the ground.
8. A parachute retardation device according to claim 7, which further includes an activating mechanism for activating the retraction device in response to a signal received from the sensing means.
9. A parachute retardation device according to claim 8 wherein the retraction device is in the form of a servo-mechanism including a piston and cylinder assembly and two sets of pulleys, each set being connected to either the piston or the cylinder.
10. A parachute retardation device according to claim 9 insofar as it is dependant on claim 5 wherein the primary cable is suspended over the pulleys, with the operatively lower end of the primary cable being connected to the piston.
11. A parachute retardation device according to claim 9 insofar as it is dependant on claim 5 wherein the primary cable is suspended over the pulleys, with the operatively lower end of the primary cable being connected to the cylinder.
12. A parachute retardation device according to claims 10 or 11 wherein the retraction device further includes a gas expansion device disposed inside the cylinder to be activated by the activating mechanism, for moving the piston outwardly relative to the cylinder, to expand the retraction device and thus to draw in the primary cable.
13. A parachute retardation device substantially as herein described and as illustrated in the accompanying drawings.
14. A parachute having a retardation device according to any one of the preceding claims.
PCT/ZA2002/000036 2001-03-22 2002-03-18 Parachute retardation device WO2002076828A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
ZA2001/2414 2001-03-22
ZA200102414 2001-03-22

Publications (1)

Publication Number Publication Date
WO2002076828A1 true WO2002076828A1 (en) 2002-10-03

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/ZA2002/000036 WO2002076828A1 (en) 2001-03-22 2002-03-18 Parachute retardation device

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
CN103612763A (en) * 2013-12-03 2014-03-05 翁源华 Parachute
GB2551893A (en) * 2016-05-12 2018-01-03 Ami Ind Inc Multi-staged suspension line length parachutes

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2575387A (en) * 1951-01-29 1951-11-20 Kluglein Helmuth Parachute
US4127246A (en) 1977-07-29 1978-11-28 Andres James R Parachute air drop load impact reducing system
FR2494664A1 (en) * 1980-11-24 1982-05-28 Honore Etienne Parachute harness for vehicle - incorporates pyrotechnic charge which forces piston down cylinder on harness to reduce landing impact
US4333621A (en) 1979-04-30 1982-06-08 Acker Otto H Shock absorbing mechanism for a parachute supported load
EP0119322A1 (en) * 1983-03-18 1984-09-26 ERNO Raumfahrttechnik Gesellschaft mit beschränkter Haftung Parachute suspension soft landing device
US6050524A (en) 1997-12-29 2000-04-18 Haggard; Roy A. Parachute soft landing system
JP2000344199A (en) * 1999-06-03 2000-12-12 Fujikura Koso Kk Parachute

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2575387A (en) * 1951-01-29 1951-11-20 Kluglein Helmuth Parachute
US4127246A (en) 1977-07-29 1978-11-28 Andres James R Parachute air drop load impact reducing system
US4333621A (en) 1979-04-30 1982-06-08 Acker Otto H Shock absorbing mechanism for a parachute supported load
FR2494664A1 (en) * 1980-11-24 1982-05-28 Honore Etienne Parachute harness for vehicle - incorporates pyrotechnic charge which forces piston down cylinder on harness to reduce landing impact
EP0119322A1 (en) * 1983-03-18 1984-09-26 ERNO Raumfahrttechnik Gesellschaft mit beschränkter Haftung Parachute suspension soft landing device
US6050524A (en) 1997-12-29 2000-04-18 Haggard; Roy A. Parachute soft landing system
JP2000344199A (en) * 1999-06-03 2000-12-12 Fujikura Koso Kk Parachute

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 2000, no. 15 6 April 2001 (2001-04-06) *

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
CN103612763A (en) * 2013-12-03 2014-03-05 翁源华 Parachute
GB2551893A (en) * 2016-05-12 2018-01-03 Ami Ind Inc Multi-staged suspension line length parachutes
US10053221B2 (en) 2016-05-12 2018-08-21 Ami Industries, Inc. Multi-staged suspension line length parachutes
GB2551893B (en) * 2016-05-12 2021-06-16 Ami Ind Inc Multi-staged suspension line length parachutes

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