CA1172228A - Gliding airfoil parachute canopy construction - Google Patents
Gliding airfoil parachute canopy constructionInfo
- Publication number
- CA1172228A CA1172228A CA000385610A CA385610A CA1172228A CA 1172228 A CA1172228 A CA 1172228A CA 000385610 A CA000385610 A CA 000385610A CA 385610 A CA385610 A CA 385610A CA 1172228 A CA1172228 A CA 1172228A
- Authority
- CA
- Canada
- Prior art keywords
- panels
- canopy
- ribs
- surface portion
- edge portion
- 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.)
- Expired
Links
- 238000010276 construction Methods 0.000 title claims description 3
- 239000004744 fabric Substances 0.000 claims description 4
- 239000000463 material Substances 0.000 claims description 4
- 230000006872 improvement Effects 0.000 claims 2
- 101000714541 Danio rerio Cadherin-2 Proteins 0.000 description 6
- 238000009826 distribution Methods 0.000 description 2
- 239000000725 suspension Substances 0.000 description 2
- 238000005520 cutting process Methods 0.000 description 1
- 230000000694 effects Effects 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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
ABSTRACT OF THE DISCLOSURE
The outer airfoil surface portions of a forward gliding type parachute canopy are made from flexible panels secured to each other along chordwise extending seams in transverse intersecting relation to spanwise extending seams connecting spaced ribs to the outer surface portions to form internal airflow channels. Each panel is substantially equal in length to the spanwise dimension of the canopy.
The outer airfoil surface portions of a forward gliding type parachute canopy are made from flexible panels secured to each other along chordwise extending seams in transverse intersecting relation to spanwise extending seams connecting spaced ribs to the outer surface portions to form internal airflow channels. Each panel is substantially equal in length to the spanwise dimension of the canopy.
Description
7 32,~
This invention relates generally to forward glide types of para-chute canopies that are ram air inflated to an airfoil shape, and more particularly to construction of such parachute canopies.
Parachute canopies of the foregoing type are made from a minimum of five to seven elongated flexible panels sewn to each other along chordwise seams extending between leading and trailing edges of the canopy. The panels must not only be dimensioned in length substantially equal to the chordwise dimensions of the canopy but must be cut to an appropriate width so that the seams between panels will coincide with chordwise seams at which ribs are connected to the airfoil surface portions. Such a constructional arrangement was heretofore deemed necessary to form a canopy with optimum stress distribu-tion under forces experienced by ram air inflated, gliding airfoil canopies.
It is therefore an important object of the present invention to provide a more efficient constructional arrangement for canopies of the aforementioned type whereby the amount of wasted material, the mlmber of seams and material cutting operations may be reduced.
The foregoing objectives have been achieved unexpectedly through use of a constructional arrangement for canopies of the ram air inflated airfoil-shaped type that is different from the basic arrangement hereto-fore utilized in that the outer airfoil surface portions are formed from elongated flexible panels sewn to each other along seams extending chord-wise in transverse intersecting relation to the seams connecting the spaced internal ribs to the outer airfoil surface portions. The uninterrupted lengths of the panels are therefore substantially equal to the spanwise dimensions of the canopy and the side edges of the panels sewn to each other need not be cut or located in any particular relationship to the rib seams as in the case of prior art constructional arrangements. A reduction in the number of panels necessary to form an airfoil surface portion may thereby be realized as well as a reduction in the number of seams.
The concept of merely arranging continuous flexible panels ~ ~ 722~,~
lengthwise in a spanwise direction for hemispherical canopies is already known, as shown in U.S. Patent No. 2,959,385 and for sail wing canopies as shown in U.S. Patent No. 3,830,512. However, significantly different stress distributions are associated with hemispherical and sail wing canopies as compared to inflated airfoil shaped canopies. Further, none of such hemispherical sail wing canopies have airfoil forming ribs associated therewith that heretofore dictated an arrangement of panels with chordwise extending seams therebetween. Accordingly, the advantages resulting from the spanwise arrangement of panels in accordance with the present invention, were not applicable to hemispherical and sail wing canopies.
Figure 1 is a perspective view of a parachute canopy constructed i in accordance with the present invention.
Figure 2 is a top plan view of the canopy shown in Figure 1.
Figure 3 is a section view taken substantially through a plane indicated by section line 3--3 in Figure 2.
Referring now to the drawings in detail, a gliding type of airfoil shaped parachute canopy is shown generally referred to by reference numeral 10. The canopy ifi connected during deployment to a payload (not shown) by means of suspension lines 12. In this type of parachute, the canopy is inflated to and maintained in an airfoil shape by means of a ram air effect during forward glide descent.
In the illustrated embodiment, the canopy 10 irlcludes an outer airfoil surface formed by an upper flexible skin generally denoted as 14 and a bottom sheet 16 from which the suspension lines extend. Such outer surface portions 14 and 16 are usually made of a flexible material or fabric extending lengthwise from a leading edge portion 18 to a trailing edge portion 20. When inflated, the outer surface portions of the canopy are held spaced apart by spanwise spaced ribs 22 secured thereto along chord-wise extending seams 24.
Heretofore, the outer surface portions of the canopy were madefrom a minimum of five to seven flexible panels of fabric elongated in the chordwise direction and sewn to each other along chordwise e~tending seams in contrast to the arrangement shown herein, wherein flexible elongated panels are sewn to each other along spanwise extending seams 26 in trans-verse intersecting relation to the chordwise extending rib seams 24. Three panels consisting of end panels 28 and 30 and intermediate panel 32 are utilized to form the outer surface portions 14 and 16. Each of the panels i 3 L
A 28, 30 and ~ therefore has an uninterrupted length that is substantially equal to the spanwise dimension of the canopy, with the sides of adjacent panels secured to each other along the spanwise extending seams 26. The unattached sides of the end panels 28 and 30 form the leading and trailing edge portions of the canopy. The unattached sides of the end panels 28 respectively associated with the upper skin 14 and bottom sheet 16 also respectively associated with the upper skin 14 and bottom sheet 16 also define the inlet opening at the leading edge portion through which inflow of air is conducted into the airflow channels between the ribs 22 causing inflation of the canopy to the airfoil shape shown. The ribs 22 may be located in spaced relation to each other wherever desired without regard to the location of the connecting seams 26 between the panels because of the transverse intersecting relationship between seams 24 and 26.
This invention relates generally to forward glide types of para-chute canopies that are ram air inflated to an airfoil shape, and more particularly to construction of such parachute canopies.
Parachute canopies of the foregoing type are made from a minimum of five to seven elongated flexible panels sewn to each other along chordwise seams extending between leading and trailing edges of the canopy. The panels must not only be dimensioned in length substantially equal to the chordwise dimensions of the canopy but must be cut to an appropriate width so that the seams between panels will coincide with chordwise seams at which ribs are connected to the airfoil surface portions. Such a constructional arrangement was heretofore deemed necessary to form a canopy with optimum stress distribu-tion under forces experienced by ram air inflated, gliding airfoil canopies.
It is therefore an important object of the present invention to provide a more efficient constructional arrangement for canopies of the aforementioned type whereby the amount of wasted material, the mlmber of seams and material cutting operations may be reduced.
The foregoing objectives have been achieved unexpectedly through use of a constructional arrangement for canopies of the ram air inflated airfoil-shaped type that is different from the basic arrangement hereto-fore utilized in that the outer airfoil surface portions are formed from elongated flexible panels sewn to each other along seams extending chord-wise in transverse intersecting relation to the seams connecting the spaced internal ribs to the outer airfoil surface portions. The uninterrupted lengths of the panels are therefore substantially equal to the spanwise dimensions of the canopy and the side edges of the panels sewn to each other need not be cut or located in any particular relationship to the rib seams as in the case of prior art constructional arrangements. A reduction in the number of panels necessary to form an airfoil surface portion may thereby be realized as well as a reduction in the number of seams.
The concept of merely arranging continuous flexible panels ~ ~ 722~,~
lengthwise in a spanwise direction for hemispherical canopies is already known, as shown in U.S. Patent No. 2,959,385 and for sail wing canopies as shown in U.S. Patent No. 3,830,512. However, significantly different stress distributions are associated with hemispherical and sail wing canopies as compared to inflated airfoil shaped canopies. Further, none of such hemispherical sail wing canopies have airfoil forming ribs associated therewith that heretofore dictated an arrangement of panels with chordwise extending seams therebetween. Accordingly, the advantages resulting from the spanwise arrangement of panels in accordance with the present invention, were not applicable to hemispherical and sail wing canopies.
Figure 1 is a perspective view of a parachute canopy constructed i in accordance with the present invention.
Figure 2 is a top plan view of the canopy shown in Figure 1.
Figure 3 is a section view taken substantially through a plane indicated by section line 3--3 in Figure 2.
Referring now to the drawings in detail, a gliding type of airfoil shaped parachute canopy is shown generally referred to by reference numeral 10. The canopy ifi connected during deployment to a payload (not shown) by means of suspension lines 12. In this type of parachute, the canopy is inflated to and maintained in an airfoil shape by means of a ram air effect during forward glide descent.
In the illustrated embodiment, the canopy 10 irlcludes an outer airfoil surface formed by an upper flexible skin generally denoted as 14 and a bottom sheet 16 from which the suspension lines extend. Such outer surface portions 14 and 16 are usually made of a flexible material or fabric extending lengthwise from a leading edge portion 18 to a trailing edge portion 20. When inflated, the outer surface portions of the canopy are held spaced apart by spanwise spaced ribs 22 secured thereto along chord-wise extending seams 24.
Heretofore, the outer surface portions of the canopy were madefrom a minimum of five to seven flexible panels of fabric elongated in the chordwise direction and sewn to each other along chordwise e~tending seams in contrast to the arrangement shown herein, wherein flexible elongated panels are sewn to each other along spanwise extending seams 26 in trans-verse intersecting relation to the chordwise extending rib seams 24. Three panels consisting of end panels 28 and 30 and intermediate panel 32 are utilized to form the outer surface portions 14 and 16. Each of the panels i 3 L
A 28, 30 and ~ therefore has an uninterrupted length that is substantially equal to the spanwise dimension of the canopy, with the sides of adjacent panels secured to each other along the spanwise extending seams 26. The unattached sides of the end panels 28 and 30 form the leading and trailing edge portions of the canopy. The unattached sides of the end panels 28 respectively associated with the upper skin 14 and bottom sheet 16 also respectively associated with the upper skin 14 and bottom sheet 16 also define the inlet opening at the leading edge portion through which inflow of air is conducted into the airflow channels between the ribs 22 causing inflation of the canopy to the airfoil shape shown. The ribs 22 may be located in spaced relation to each other wherever desired without regard to the location of the connecting seams 26 between the panels because of the transverse intersecting relationship between seams 24 and 26.
Claims (6)
1. For use in a forward gliding parachute having a ram air inflated canopy, including an uninterrupted top flexible surface portion extending chordwise between a leading edge portion and a trailing edge portion and a plurality of spanwise spaced ribs depending from the top surface portion to form airflow channels therebetween through which airflow is conducted from the leading edge portion toward the trailing edge portion to inflate the canopy into an airfoil shape; the improve-ment residing in construction of said canopy from a plurality of elongated panels of uninterrupted fabric to form said top surface portion and securing means interconnecting said panels at connecting seams extending spanwise in transverse relation to the ribs.
2. The combination of claim 1 wherein said ribs are secured to the panels in intersecting relation to said connecting seams between the panels.
3. The combination of claim 2 wherein said canopy includes a bottom surface portion spaced from the top surface portion by said ribs, said bottom surface portion being formed from a plurality of elongated panels of uninterrupted fabric secured to each other along connecting seams extending transverse to the ribs, one of the panels associated with each of the top and bottom surface portions having elongated sides at the leading edge portion forming an inlet opening to the airflow channels.
4. The improvement as defined in claim 1 wherein each of said panels is made of an uninterrupted, unitary piece of flexible material having spaced sides substantially equal in spanwise dimension to the canopy, at which the connecting seams are located.
5. The combination of claim 4 wherein said outer airfoil surface portion of the canopy includes an upper skin from which the ribs depend.
6. The combination of claim 5 wherein said outer airfoil surface portion further includes a bottom sheet to which the ribs are secured, one of the panels associated with each of the upper skin and bottom sheet having unattached sides spaced from each other at the leading edge portion of the canopy to form an inlet opening into airflow inflating channels formed between the ribs.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US18975080A | 1980-09-23 | 1980-09-23 | |
| US189,750 | 1980-09-23 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1172228A true CA1172228A (en) | 1984-08-07 |
Family
ID=22698614
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA000385610A Expired CA1172228A (en) | 1980-09-23 | 1981-09-10 | Gliding airfoil parachute canopy construction |
Country Status (9)
| Country | Link |
|---|---|
| KR (1) | KR890000531B1 (en) |
| AU (1) | AU528256B2 (en) |
| CA (1) | CA1172228A (en) |
| DE (1) | DE3137304C2 (en) |
| FR (1) | FR2490587A1 (en) |
| GB (1) | GB2084090B (en) |
| IL (1) | IL63867A (en) |
| IT (1) | IT1139465B (en) |
| ZA (1) | ZA816329B (en) |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2141079B (en) * | 1983-06-10 | 1987-07-29 | Para Flite Inc | Canopy loading system for ram air parachutes |
| GB8505204D0 (en) * | 1985-02-28 | 1985-04-03 | Harley Chutes Ltd | Parachute |
| AU572424B1 (en) * | 1987-10-02 | 1988-05-05 | Parachutes Australia Pty. Ltd. | Ram air parachute |
| FR2624828B1 (en) * | 1987-12-21 | 1990-05-11 | Laser Lab Sarl | SADDLE HARNESS FOR PARACHUTE OF THE FLEXIBLE WING TYPE |
| GB2295132A (en) * | 1994-11-17 | 1996-05-22 | Darren Arkwright | Wing construction |
| US6929221B2 (en) * | 2002-12-09 | 2005-08-16 | Atair Aerospace Inc. | Ram air parachute with tensioned top skin |
| WO2005014392A1 (en) * | 2003-08-07 | 2005-02-17 | Peter Lynn Limited | Ram air-inflated kite |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2959385A (en) * | 1957-06-25 | 1960-11-08 | Walter C Buhler | Stressed skin parachute |
| US3131894A (en) * | 1963-01-10 | 1964-05-05 | Domina C Jalbert | Multi-cell glide canopy parachute |
| US3524613A (en) * | 1968-04-08 | 1970-08-18 | Pioneer Parachute Co Inc | Flexible gliding wing |
| US3724789A (en) * | 1970-02-02 | 1973-04-03 | S Snyder | Ram air glide parachute |
| AT310063B (en) * | 1971-12-28 | 1973-09-10 | Ver Baubeschlag Gretsch Co | Brake sails for skiers |
| US3822844A (en) * | 1973-06-25 | 1974-07-09 | Jack Sutton | Parachute |
-
1981
- 1981-09-10 CA CA000385610A patent/CA1172228A/en not_active Expired
- 1981-09-11 ZA ZA816329A patent/ZA816329B/en unknown
- 1981-09-11 GB GB8127552A patent/GB2084090B/en not_active Expired
- 1981-09-14 AU AU75218/81A patent/AU528256B2/en not_active Expired
- 1981-09-17 DE DE3137304A patent/DE3137304C2/en not_active Expired
- 1981-09-17 IL IL63867A patent/IL63867A/en not_active IP Right Cessation
- 1981-09-22 FR FR8118169A patent/FR2490587A1/en active Granted
- 1981-09-22 IT IT24072/81A patent/IT1139465B/en active
- 1981-09-22 KR KR8103544A patent/KR890000531B1/en active
Also Published As
| Publication number | Publication date |
|---|---|
| DE3137304A1 (en) | 1982-05-27 |
| DE3137304C2 (en) | 1983-10-13 |
| AU528256B2 (en) | 1983-04-21 |
| ZA816329B (en) | 1982-11-24 |
| GB2084090B (en) | 1984-06-27 |
| IT8124072A0 (en) | 1981-09-22 |
| IL63867A (en) | 1985-09-29 |
| AU7521881A (en) | 1982-04-01 |
| GB2084090A (en) | 1982-04-07 |
| KR890000531B1 (en) | 1989-03-20 |
| IT1139465B (en) | 1986-09-24 |
| KR830007361A (en) | 1983-10-19 |
| FR2490587B1 (en) | 1985-01-25 |
| FR2490587A1 (en) | 1982-03-26 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| MKEC | Expiry (correction) | ||
| MKEX | Expiry |