CA1190434A - Wing housing and cover release assembly for self- erecting wing - Google Patents
Wing housing and cover release assembly for self- erecting wingInfo
- Publication number
- CA1190434A CA1190434A CA000411465A CA411465A CA1190434A CA 1190434 A CA1190434 A CA 1190434A CA 000411465 A CA000411465 A CA 000411465A CA 411465 A CA411465 A CA 411465A CA 1190434 A CA1190434 A CA 1190434A
- Authority
- CA
- Canada
- Prior art keywords
- wing
- housing
- housing structure
- latch
- erecting
- 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
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/02—Stabilising arrangements
- F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
- F42B10/146—Fabric fins, i.e. fins comprising at least one spar and a fin cover made of flexible sheet material
-
- E—FIXED CONSTRUCTIONS
- E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
- E05C—BOLTS OR FASTENING DEVICES FOR WINGS, SPECIALLY FOR DOORS OR WINDOWS
- E05C9/00—Arrangements of simultaneously actuated bolts or other securing devices at well-separated positions on the same wing
- E05C9/02—Arrangements of simultaneously actuated bolts or other securing devices at well-separated positions on the same wing with one sliding bar for fastening when moved in one direction and unfastening when moved in opposite direction; with two sliding bars moved in the same direction when fastening or unfastening
Abstract
WING HOUSING AND COVER RELEASE ASSEMBLY
FOR SELF-ERECTING WING
ABSTRACT OF THE DISCLOSURE
A self-erecting collapsible wing for an airframe includes a telescoping strut assembly including a leading strut and a trailing strut each pivoted at an inner end to fixed pins on a base support structure of a wing housing within a slot in the airframe for retraction to a colinear position within the housing and spring biased to an outward fully deployed position. A releasable cover conforming to the curvature of the airframe is normally latched in posi-tion over the slot when the wing is in the collapsed position within the wing housing and is jettisoned to permit automatic self-erection of the wing.
FOR SELF-ERECTING WING
ABSTRACT OF THE DISCLOSURE
A self-erecting collapsible wing for an airframe includes a telescoping strut assembly including a leading strut and a trailing strut each pivoted at an inner end to fixed pins on a base support structure of a wing housing within a slot in the airframe for retraction to a colinear position within the housing and spring biased to an outward fully deployed position. A releasable cover conforming to the curvature of the airframe is normally latched in posi-tion over the slot when the wing is in the collapsed position within the wing housing and is jettisoned to permit automatic self-erection of the wing.
Description
3~
. . Y~
~1 ~ING HO11SING AND COVER RELEAS E ASSEMBLY
FOR SELF-ERECTING WING
8ACKGRWND OF TEIE ïNVENTION
The present invention relates lto rockets and missiles and per~ains particularly to collapsible wing s~ructures for such missiles.
Many rockets and missiles u illze some form of wing or stabilizer structure for stabilizing the mis~ile during 1~ 1ight. Missiles are requently stored and launched from tubular laun~hers and are frequently deployed from aircraft or other missiles. ~nder such circumstances it ~5 fEe-quently necessary to minimize ~he space ~or the mi5sile until it is launched~ Folding wings of various types and configurations have been utilized in the past to minimize the space required for such missiles.
The premium for space requires that ~he folding or collapsin~ wing structures be foldable or collapsable to a minimum space. In addition~ the ~light characteristics o the missile require opti~num reliability and performance o~
the deployed wing struc~ure. It i~ therefore de~irable that the folding wing structure have highly efficient flight characteristics and, at the same time, be foldable to a minimum space~
A cavity or wing housing mus be provided within the airframe s~ruc~ure for ~ontaining the folded wing and open to the exterior of 'che air~rame to permit extension of the wing. A reliable closure must be proYided for the openlng !~
. . Y~
~1 ~ING HO11SING AND COVER RELEAS E ASSEMBLY
FOR SELF-ERECTING WING
8ACKGRWND OF TEIE ïNVENTION
The present invention relates lto rockets and missiles and per~ains particularly to collapsible wing s~ructures for such missiles.
Many rockets and missiles u illze some form of wing or stabilizer structure for stabilizing the mis~ile during 1~ 1ight. Missiles are requently stored and launched from tubular laun~hers and are frequently deployed from aircraft or other missiles. ~nder such circumstances it ~5 fEe-quently necessary to minimize ~he space ~or the mi5sile until it is launched~ Folding wings of various types and configurations have been utilized in the past to minimize the space required for such missiles.
The premium for space requires that ~he folding or collapsin~ wing structures be foldable or collapsable to a minimum space. In addition~ the ~light characteristics o the missile require opti~num reliability and performance o~
the deployed wing struc~ure. It i~ therefore de~irable that the folding wing structure have highly efficient flight characteristics and, at the same time, be foldable to a minimum space~
A cavity or wing housing mus be provided within the airframe s~ruc~ure for ~ontaining the folded wing and open to the exterior of 'che air~rame to permit extension of the wing. A reliable closure must be proYided for the openlng !~
2--that functions to eliminate excessive drag, to effectively contain the wing structure and to permit extensiorl of the wing without interf erence.
SU~5MARY AND OBJECTS OF T~E INVENTION
It is therefore the primary object o~ the present invention to provide an improved wing ~uppor~ structure for collapsible wings.
In accordance wi~h ~he primary aspect of the present inventiQn, a telescopic w~ng suppor~ struct~re for a col-lapsible and extensible wing structure includes inner and outer telescoping stru~ members including a leading strut and a trailing strut, being telescopically compressed tD a colinear position within a compact housing mounted Oll an airf rame and includes an opening through whioh the wings extend to the ully deployed extended position with a releasable cover that can be jettisoned to enable extension of the wings.
BRIEF DESCRI~TION OF THE DRAWINGS
The above and other objects and advantages of the present invention will become apparent f rom the following description when read in conjunctlon with the accompanying dzawings wherein:
Figure 1 iS a perspective view of a typical missile incorporating the ~elf~exec~ing wingsO
Figure 2 is a side elevat~on view of the wtng-containing section of the misslle body, wl~h the wings folded and enclosedO
Figure 3 as a top plan vlew of one wing unit in the erected posi ~ion.
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Figure 4 is a sec~ional.: view ~aken on line 4-4 of Figure 3.
Figure 5 is a sectional view talcen on line 5-5 of 5 Figure 3~
~ igure 6 is sectional view taken on line 6-6 of Figure 2.
~ igure 7 i5 an enla.rged sectional view taken on line 7-7 o:E Figure 2.
Figure 8 is a view similar to Fiyure 7, but with the cover released and the wing erected.
Figure 9 is an enlarged sectional view taken on line g-9 of Figure 4O
Figure 10 is an enlarged view similar to a portion of lS Figure S, showing the cover latch in released positiorl~, DRTAXLED DESCRIPTION OF A PREFERRED EMBODIMENT
Turning to the drawings, khere is illustra~ed in F~g~
ure 1 a missile having a generally cyl~ndrical body 10 with a nose cone 12 and a plurali~y of ~adially outwardly extending w!ngs 14 extending outwardly from a p:Lurality of circumferentially arranged lon~itudinally extending slot~
16 in the body 10. A plurality o~ guiding or steering f ins or rudders 18 extend radially outward f rom the 'cail end of the missile body.
The miss.ile can have any suitable form of guidance and propulsion systems and any required configllra~cion of war-head. The missile can be launched in any suitable manner such as from ground vehicl es or locations, aircraft~ or o~her missiles. The space saving developments of ~che 3û present invention~ however, were primarily developed f o~
utilization in missiles transported by other missiles whereln ~pace and rel;ability^is a premium.
The wings can have any suitable conf igurat;on wi~h the illustrated embodimerlt having a generally ~riangular con-5 figuration~ The wing fabric covering S6 is constructed ofa flexible or pliable material such as a ligh~we.ight nylo or dacron and is cut and sewn in a way that it precisely conforms to the supporting strut assembly in its extended posi ti orl.
10The wing assembly is self-contained and is a complete-ly operable modular unit that can be detachably mounted wi'chin the rocket body positîoned for extension or retrac-tion of the wing through a slot in the rocket bodyO The wing assembly includes a channel housing 20 having an 15 elongated multiwidth slot 22 extending the length o the housing def ining a chamber or cavity within which the wing folds. The housing 20 has an outer configuration or curva-ture conforming substantially to the shape of the surace of the missile and includes means that will be described/
20 including a disposable cover 26 for covering the retracted wing opening. Th housing body 20 includes a base plate 24 as can ~est be seen in Figures 7 throu9h 9~ The base plate 24 is detachable fLom the housing 20 and serves as the primary mounting structure for the wing strutsO The plate 2~ 24 also serves to clamp ~che wing covering ~abric between the base plate and housingn The housiny is of a depth 2nd width to receive and enclose the collapsed wing strut assembly and the fabric covering thereof and includes a detachable cover 26 as shown in ~igures 7 and B for coverin~ the retracted wing
SU~5MARY AND OBJECTS OF T~E INVENTION
It is therefore the primary object o~ the present invention to provide an improved wing ~uppor~ structure for collapsible wings.
In accordance wi~h ~he primary aspect of the present inventiQn, a telescopic w~ng suppor~ struct~re for a col-lapsible and extensible wing structure includes inner and outer telescoping stru~ members including a leading strut and a trailing strut, being telescopically compressed tD a colinear position within a compact housing mounted Oll an airf rame and includes an opening through whioh the wings extend to the ully deployed extended position with a releasable cover that can be jettisoned to enable extension of the wings.
BRIEF DESCRI~TION OF THE DRAWINGS
The above and other objects and advantages of the present invention will become apparent f rom the following description when read in conjunctlon with the accompanying dzawings wherein:
Figure 1 iS a perspective view of a typical missile incorporating the ~elf~exec~ing wingsO
Figure 2 is a side elevat~on view of the wtng-containing section of the misslle body, wl~h the wings folded and enclosedO
Figure 3 as a top plan vlew of one wing unit in the erected posi ~ion.
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Figure 4 is a sec~ional.: view ~aken on line 4-4 of Figure 3.
Figure 5 is a sectional view talcen on line 5-5 of 5 Figure 3~
~ igure 6 is sectional view taken on line 6-6 of Figure 2.
~ igure 7 i5 an enla.rged sectional view taken on line 7-7 o:E Figure 2.
Figure 8 is a view similar to Fiyure 7, but with the cover released and the wing erected.
Figure 9 is an enlarged sectional view taken on line g-9 of Figure 4O
Figure 10 is an enlarged view similar to a portion of lS Figure S, showing the cover latch in released positiorl~, DRTAXLED DESCRIPTION OF A PREFERRED EMBODIMENT
Turning to the drawings, khere is illustra~ed in F~g~
ure 1 a missile having a generally cyl~ndrical body 10 with a nose cone 12 and a plurali~y of ~adially outwardly extending w!ngs 14 extending outwardly from a p:Lurality of circumferentially arranged lon~itudinally extending slot~
16 in the body 10. A plurality o~ guiding or steering f ins or rudders 18 extend radially outward f rom the 'cail end of the missile body.
The miss.ile can have any suitable form of guidance and propulsion systems and any required configllra~cion of war-head. The missile can be launched in any suitable manner such as from ground vehicl es or locations, aircraft~ or o~her missiles. The space saving developments of ~che 3û present invention~ however, were primarily developed f o~
utilization in missiles transported by other missiles whereln ~pace and rel;ability^is a premium.
The wings can have any suitable conf igurat;on wi~h the illustrated embodimerlt having a generally ~riangular con-5 figuration~ The wing fabric covering S6 is constructed ofa flexible or pliable material such as a ligh~we.ight nylo or dacron and is cut and sewn in a way that it precisely conforms to the supporting strut assembly in its extended posi ti orl.
10The wing assembly is self-contained and is a complete-ly operable modular unit that can be detachably mounted wi'chin the rocket body positîoned for extension or retrac-tion of the wing through a slot in the rocket bodyO The wing assembly includes a channel housing 20 having an 15 elongated multiwidth slot 22 extending the length o the housing def ining a chamber or cavity within which the wing folds. The housing 20 has an outer configuration or curva-ture conforming substantially to the shape of the surace of the missile and includes means that will be described/
20 including a disposable cover 26 for covering the retracted wing opening. Th housing body 20 includes a base plate 24 as can ~est be seen in Figures 7 throu9h 9~ The base plate 24 is detachable fLom the housing 20 and serves as the primary mounting structure for the wing strutsO The plate 2~ 24 also serves to clamp ~che wing covering ~abric between the base plate and housingn The housiny is of a depth 2nd width to receive and enclose the collapsed wing strut assembly and the fabric covering thereof and includes a detachable cover 26 as shown in ~igures 7 and B for coverin~ the retracted wing
3~
pocketO The wing housing is mounted at an opening in the sk in of the m i ss il e I
The support strut assembly ~Eor the wing :Eabric is best seen in Figure 4 and includes a forward strut assembly 5 pivotally mounted or hinged on a forward hinge bracket 28 mounted tQ the forward end of the hottom plate 24 and a trailing strut pivotally mounted to a trailing hinge brack-et 30 secured to the bottom plate 24. The ~orward strut ~ncludes a lower outer tubular strut member 32 pivotally mounted or hinged to the bracket 28 and telescopingly receiving an inner upper tubular strut member 34 which i5 pivotally secured by means of a hinge pin 36 at the outer end to the trailing strutO A compression spring 38 is mounted within the bore of both the lower and upper tubular members 32 and 34 and extends substantially the full length thereof. This s'pring is preferably under sufficient com-pression at its ou ermost positlon to retain the strut in its extended position under normal circumstances.
The trailing stru~c is substantially identical to the 20 leading s~rut including a lower tubular strut member 40 hinged to the hinge bracket 30 and telescopingly receiving a tubular inner or upper tubular strut member 42. A com-pression s!?ring 44 is confined within the bore of the tubul~r members and extends substantially the full length 25 'chereof and simi~ arly is under su~icient compression a'c its outermost position for retaining the strut in its extended pos i ti on,, The outer end of inner strut mernber 34 includes a bifurcated hinge bracket member 4~ receiving a hinge member 3û 48 of the inner strut member 4~.
~6--Each strut is provided with an extension or anticol-lapse lock (not shown) to pr~vent the wing loading f rom compressing the ~trut. These locks are formed as fingers by cuttin~ a narrow ~-shaped slot in the wall of the upper S strut member. The finger bent outward with its free end pointing toward the open end of the upper strut 34 or 42 such that when biased outward it engages the outer end of the outer strut member 32 or 40.
At least one of the struts is provided with an anti-rotation--lock to preven~ accidental rot~tion of the outer strut members when the stru~s are in a colinear or col-lapsed positionO Turning to Figures 4 and 6, antirotation locks are provided and each respeotively consists of pins 54 and 56 extending outward from ~he upper strut me~ber at 15 a position to engage slots 58 and and 60 at the outer end of the lower strut members 32 and 40 upon complete collapse of the strut assembly to the colinear position as shown in Figure 6~ Although ~wo locks are illustrated, one for each strut, a single lock would appear to serve the purpose 20 in most instances.
Turning now to Figure 4, a leaf spring 62 is disposed or mounted on the base plate 24 disposed directly beneath the strut assembly for engaging and applying a force to the strut assembly below the hinge pin 36 upon folding of the 25 struts ~o the collapsed posi~ion as shown in ~igure 6.
This spring 62 provides an initial outward ~hrust or force on the struts preventing them from locking in the collapsed positionO
The fabric oover 66 of the wing, as previousl~ dis-cussed~ is shaped to encompass the strut structure and ~ ~1 ~ A ~
includes ~ base portion or sklrt portion 67 that is secured to the wing housing 20 by clamping between the base plate 24 and the housing and ~ncluding peripheral clamp pla~es 64 as can be ;een in Figures 7 and 80 These ensure 5 a secur~ attachment of the wing fabr~ c to the winq housing., The above describe~ wing struc~ure can be collapsed into a folded position and the ~abric covering rolled within the winy housing as shown in Figure 7q This is accomplished by compressing the strut locks and apply:;ng a lû force at the tip oE the wing in a direction that ~elescop-ically compresses or collapses the two struts. The struts become progre~sively sho~ter - and pivo ab~ut the lower hinge pins until they reach ~he fully folded or collapsed position where the~ are colinear ar,d lying against the base 15 plate 24 as showll in Figures 6 and 7~ At this point~ the compression springs 38 and 44 within the two struts are fully cvmpressed to very near . their solid heights a'c which position they deliver their maximum forceq ~ith the struts in this position, however, the spring force is in a direc-20 tion colinear ~r coaxially t~ereof and does not tend to force the wings openO In order to initiate unfold.ing ~f the winys, it is necessary to bias or force the stru~ ~rom this posi'cionO This is accomplished by means of the leaf spring 62 applying a force biasir~g the s.ruts ~ small 25 distance outward such that ~he compression springs within the stru~s act ~co quic:kly snap the wing o~l~ward to its fully extended position~ The spring 62 is positioned and shaped~ as shown in Figure 4, such that when the struts are CD~ ~
V ~3 ~
in a fully collapsed position as shown in Figure 6 the ~pring is loaded to provide an initial ~orce for extension of the struts and wing assembly.
A releasable cover extends over and covers the opening S over the folded wing s~ructure as best sPen~ for example, in Figures 2, 6 and 7O This wing cover 26 comprises an elonga~ed generally rec~angular plate covering the houslng opening when the wing is folded therein. The wing coYer 26 as best seen in Figures 7 and 8 includes a plural ity of hinge tabs 68 on and extending along one side of the cover And a plurality of latch tabs 70 extending along the other side of the cover. The hinge tabs 68 fit under the hinge pins 72~ The latch tabs 70 extend beneath and engage latch fîngers 80 on the latch plate 76. The upper surface of the lS cover as seen in ~igure 7 is ~urved to conform generally to the configuration of the missile housing ~o provide mini-mum resistance to air flow and to elimina'ce space occupying protruberances.
As best seen in Figure 3~ a plurality of hinge pins 72 2Q are mounted in a plurality oE slots or depressions 74 along one side of the wing housing and are engaged by the hing~
tabs 68. A slideable latch plate 76 as shown in Figl~res 5 and 10 is secured by means of a plurality of 510ts 78 and shoulder screws 79 to the opposite side wall of the housing with a plurality of latch fingers 80 biased ts a position (latched positiQn) overlapping a plurality of tab receiving slots 82 in the sidewall o the housing. The latch plate is biased to thP latched position with f ingers 80 overlap-ping and engaging ~ atch tabs 70 by means of a coTnpresslon 30 spring 84 a~ one end or the plate and housing. A plunyer ~S L~
~9_ B6 within a cylinder 87 engaying the end o the latch plate is provided with a small explosive charge 88 within a chamber whi~-h i5 ignited to shift the latch plate to ~he released position for release of the cover 26. This shîft-5 ing of the lateh plate permits the wing assembly to extendoutward forcing the cover to pivot outward about hinge pins 72 and release from its hinged position and be swept a~ay by airflow along the missile body. The wing is then free to snap out to its fully deployed position.
~hile we have illustrated and described our invention by means of specific embodiments, it is to be understood that numerous changes and modif ications may be made therei without departing from the spirit and scope of the inven-tion as def ined in the appended claims.
pocketO The wing housing is mounted at an opening in the sk in of the m i ss il e I
The support strut assembly ~Eor the wing :Eabric is best seen in Figure 4 and includes a forward strut assembly 5 pivotally mounted or hinged on a forward hinge bracket 28 mounted tQ the forward end of the hottom plate 24 and a trailing strut pivotally mounted to a trailing hinge brack-et 30 secured to the bottom plate 24. The ~orward strut ~ncludes a lower outer tubular strut member 32 pivotally mounted or hinged to the bracket 28 and telescopingly receiving an inner upper tubular strut member 34 which i5 pivotally secured by means of a hinge pin 36 at the outer end to the trailing strutO A compression spring 38 is mounted within the bore of both the lower and upper tubular members 32 and 34 and extends substantially the full length thereof. This s'pring is preferably under sufficient com-pression at its ou ermost positlon to retain the strut in its extended position under normal circumstances.
The trailing stru~c is substantially identical to the 20 leading s~rut including a lower tubular strut member 40 hinged to the hinge bracket 30 and telescopingly receiving a tubular inner or upper tubular strut member 42. A com-pression s!?ring 44 is confined within the bore of the tubul~r members and extends substantially the full length 25 'chereof and simi~ arly is under su~icient compression a'c its outermost position for retaining the strut in its extended pos i ti on,, The outer end of inner strut mernber 34 includes a bifurcated hinge bracket member 4~ receiving a hinge member 3û 48 of the inner strut member 4~.
~6--Each strut is provided with an extension or anticol-lapse lock (not shown) to pr~vent the wing loading f rom compressing the ~trut. These locks are formed as fingers by cuttin~ a narrow ~-shaped slot in the wall of the upper S strut member. The finger bent outward with its free end pointing toward the open end of the upper strut 34 or 42 such that when biased outward it engages the outer end of the outer strut member 32 or 40.
At least one of the struts is provided with an anti-rotation--lock to preven~ accidental rot~tion of the outer strut members when the stru~s are in a colinear or col-lapsed positionO Turning to Figures 4 and 6, antirotation locks are provided and each respeotively consists of pins 54 and 56 extending outward from ~he upper strut me~ber at 15 a position to engage slots 58 and and 60 at the outer end of the lower strut members 32 and 40 upon complete collapse of the strut assembly to the colinear position as shown in Figure 6~ Although ~wo locks are illustrated, one for each strut, a single lock would appear to serve the purpose 20 in most instances.
Turning now to Figure 4, a leaf spring 62 is disposed or mounted on the base plate 24 disposed directly beneath the strut assembly for engaging and applying a force to the strut assembly below the hinge pin 36 upon folding of the 25 struts ~o the collapsed posi~ion as shown in ~igure 6.
This spring 62 provides an initial outward ~hrust or force on the struts preventing them from locking in the collapsed positionO
The fabric oover 66 of the wing, as previousl~ dis-cussed~ is shaped to encompass the strut structure and ~ ~1 ~ A ~
includes ~ base portion or sklrt portion 67 that is secured to the wing housing 20 by clamping between the base plate 24 and the housing and ~ncluding peripheral clamp pla~es 64 as can be ;een in Figures 7 and 80 These ensure 5 a secur~ attachment of the wing fabr~ c to the winq housing., The above describe~ wing struc~ure can be collapsed into a folded position and the ~abric covering rolled within the winy housing as shown in Figure 7q This is accomplished by compressing the strut locks and apply:;ng a lû force at the tip oE the wing in a direction that ~elescop-ically compresses or collapses the two struts. The struts become progre~sively sho~ter - and pivo ab~ut the lower hinge pins until they reach ~he fully folded or collapsed position where the~ are colinear ar,d lying against the base 15 plate 24 as showll in Figures 6 and 7~ At this point~ the compression springs 38 and 44 within the two struts are fully cvmpressed to very near . their solid heights a'c which position they deliver their maximum forceq ~ith the struts in this position, however, the spring force is in a direc-20 tion colinear ~r coaxially t~ereof and does not tend to force the wings openO In order to initiate unfold.ing ~f the winys, it is necessary to bias or force the stru~ ~rom this posi'cionO This is accomplished by means of the leaf spring 62 applying a force biasir~g the s.ruts ~ small 25 distance outward such that ~he compression springs within the stru~s act ~co quic:kly snap the wing o~l~ward to its fully extended position~ The spring 62 is positioned and shaped~ as shown in Figure 4, such that when the struts are CD~ ~
V ~3 ~
in a fully collapsed position as shown in Figure 6 the ~pring is loaded to provide an initial ~orce for extension of the struts and wing assembly.
A releasable cover extends over and covers the opening S over the folded wing s~ructure as best sPen~ for example, in Figures 2, 6 and 7O This wing cover 26 comprises an elonga~ed generally rec~angular plate covering the houslng opening when the wing is folded therein. The wing coYer 26 as best seen in Figures 7 and 8 includes a plural ity of hinge tabs 68 on and extending along one side of the cover And a plurality of latch tabs 70 extending along the other side of the cover. The hinge tabs 68 fit under the hinge pins 72~ The latch tabs 70 extend beneath and engage latch fîngers 80 on the latch plate 76. The upper surface of the lS cover as seen in ~igure 7 is ~urved to conform generally to the configuration of the missile housing ~o provide mini-mum resistance to air flow and to elimina'ce space occupying protruberances.
As best seen in Figure 3~ a plurality of hinge pins 72 2Q are mounted in a plurality oE slots or depressions 74 along one side of the wing housing and are engaged by the hing~
tabs 68. A slideable latch plate 76 as shown in Figl~res 5 and 10 is secured by means of a plurality of 510ts 78 and shoulder screws 79 to the opposite side wall of the housing with a plurality of latch fingers 80 biased ts a position (latched positiQn) overlapping a plurality of tab receiving slots 82 in the sidewall o the housing. The latch plate is biased to thP latched position with f ingers 80 overlap-ping and engaging ~ atch tabs 70 by means of a coTnpresslon 30 spring 84 a~ one end or the plate and housing. A plunyer ~S L~
~9_ B6 within a cylinder 87 engaying the end o the latch plate is provided with a small explosive charge 88 within a chamber whi~-h i5 ignited to shift the latch plate to ~he released position for release of the cover 26. This shîft-5 ing of the lateh plate permits the wing assembly to extendoutward forcing the cover to pivot outward about hinge pins 72 and release from its hinged position and be swept a~ay by airflow along the missile body. The wing is then free to snap out to its fully deployed position.
~hile we have illustrated and described our invention by means of specific embodiments, it is to be understood that numerous changes and modif ications may be made therei without departing from the spirit and scope of the inven-tion as def ined in the appended claims.
Claims (10)
1. In an airframe having a self-erecting wing structure, a wing housing structure com-prising:
means defining a compartment for containing a self-erecting wing in a collapsed condition and an opening through which said self-erecting wing extends upon erecting;
a cover releasably mounted over said opening;
and releasable latching means for retaining said cover in position over said opening.
means defining a compartment for containing a self-erecting wing in a collapsed condition and an opening through which said self-erecting wing extends upon erecting;
a cover releasably mounted over said opening;
and releasable latching means for retaining said cover in position over said opening.
2. The wing housing structure of Claim 1 wherein:
said compartment is elongated and extends generally along the axis of the airframe; and said latching means includes fixed latch-ing means extending along one side of said housing adjacent said opening; and moveable latching means extending along the other side of said housing adjacent said opening.
said compartment is elongated and extends generally along the axis of the airframe; and said latching means includes fixed latch-ing means extending along one side of said housing adjacent said opening; and moveable latching means extending along the other side of said housing adjacent said opening.
3. The wing housing structure of Claim 2 wherein:
said fixed latching means includes a plural-ity of hinge pins; and said moveable latching means comprises a slideable latching plate normally biased to a latched position.
said fixed latching means includes a plural-ity of hinge pins; and said moveable latching means comprises a slideable latching plate normally biased to a latched position.
4. The wing housing structure of Claim 3 wherein:
said cover includes a plurality of hinge tabs for engaging said hinge pins; and a plurality of latch tabs for engaging said latch plate.
said cover includes a plurality of hinge tabs for engaging said hinge pins; and a plurality of latch tabs for engaging said latch plate.
5. The wing housing structure of Claim 4 wherein:
said latch plate includes a plurality of latch fingers for extending over said latch tabs on said cover in said latched position.
said latch plate includes a plurality of latch fingers for extending over said latch tabs on said cover in said latched position.
6. The wing housing structure of Claim 5 including shifting means for shifting said latching plate to the unlatched position for releasing said cover.
7. The wing housing structure of Claim 6, wherein:
said shifting means comprises a cylinder, a piston reciprocably mounted in said cylinder and operatively connected to said latch plate; and means for generating a gas pressure in said cylinder for forcing said piston outward and shift-ing said latch plate to the unlatched position.
said shifting means comprises a cylinder, a piston reciprocably mounted in said cylinder and operatively connected to said latch plate; and means for generating a gas pressure in said cylinder for forcing said piston outward and shift-ing said latch plate to the unlatched position.
8. The wing housing structure of Claim 7 wherein said housing means includes a detachable base plate; and a collapsible wing mounted on said base plate and collapsible to a position completely within said housing.
9. The wing housing structure of Claim 8 wherein:
said wing includes a plurality of telescoping struts mounted on said base plate;
a fabric covering covering said struts and shaped to the configuration of the erected wing.
said wing includes a plurality of telescoping struts mounted on said base plate;
a fabric covering covering said struts and shaped to the configuration of the erected wing.
10. The wing housing structure of Claim 9 wherein:
said wing covering is anchored to said housing by means of said base plate.
said wing covering is anchored to said housing by means of said base plate.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US34766082A | 1982-02-10 | 1982-02-10 | |
| US347,660 | 1982-02-10 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1190434A true CA1190434A (en) | 1985-07-16 |
Family
ID=23364680
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA000411465A Expired CA1190434A (en) | 1982-02-10 | 1982-09-15 | Wing housing and cover release assembly for self- erecting wing |
Country Status (17)
| Country | Link |
|---|---|
| JP (1) | JPS58138998A (en) |
| KR (1) | KR860000220B1 (en) |
| AU (1) | AU530408B2 (en) |
| BE (1) | BE894382A (en) |
| CA (1) | CA1190434A (en) |
| CH (1) | CH661347A5 (en) |
| DE (1) | DE3234269C2 (en) |
| DK (1) | DK153183C (en) |
| ES (1) | ES8308060A1 (en) |
| FR (1) | FR2521281B1 (en) |
| GB (1) | GB2115117B (en) |
| HK (1) | HK36588A (en) |
| IL (1) | IL66624A (en) |
| IT (1) | IT1149076B (en) |
| NL (1) | NL184340C (en) |
| NO (1) | NO150820C (en) |
| SE (1) | SE452364B (en) |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3403573A1 (en) * | 1983-11-09 | 1985-08-08 | Diehl GmbH & Co, 8500 Nürnberg | BULLET WITH FOLD-OUT WINGS |
| GB8815060D0 (en) * | 1988-06-24 | 1988-11-16 | British Aerospace | Fin assembly for projectile |
| DE3918244A1 (en) * | 1989-06-05 | 1990-12-06 | Diehl Gmbh & Co | FOLDING WING FROM A MISSILE |
| DE4105142A1 (en) * | 1991-02-20 | 1992-08-27 | Diehl Gmbh & Co | PROJECTILE WITH FOLD-OUT PAD |
| FR2721702B1 (en) * | 1994-06-28 | 1996-08-14 | Luchaire Defense Sa | Device for deploying a projectile fin. |
| DE102004007311A1 (en) | 2004-02-14 | 2005-09-01 | Diehl Bgt Defence Gmbh & Co. Kg | Projectile with wings that can be folded away from the projectile fuselage |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1715558A (en) * | 1929-06-04 | X t trunk lock | ||
| FR1490554A (en) * | 1966-05-03 | 1967-08-04 | Ruggieri Ets | Development of deploying rocket stabilizers |
| US3853288A (en) * | 1967-07-17 | 1974-12-10 | H Bode | Encasement for the tail section of a rocket with a central nozzle and extendible control vanes |
| BE756110A (en) * | 1970-09-14 | 1971-02-15 | Gohlke Werner | DEVICE FOR THE THERMAL INFLUENCE OF FLYING GEAR FUNCTIONS. |
| DE2623562A1 (en) * | 1976-05-26 | 1977-12-08 | Basf Ag | PROCESS FOR MANUFACTURING GLYCOLESTERS AND THEIR SUBSEQUENT PRODUCTS |
| US4351499A (en) * | 1979-09-24 | 1982-09-28 | General Dynamics | Double fabric, retractable, self-erecting wing for missle |
-
1982
- 1982-08-23 IL IL66624A patent/IL66624A/en not_active IP Right Cessation
- 1982-09-07 GB GB08225459A patent/GB2115117B/en not_active Expired
- 1982-09-10 NL NLAANVRAGE8203531,A patent/NL184340C/en not_active IP Right Cessation
- 1982-09-13 BE BE0/209001A patent/BE894382A/en not_active IP Right Cessation
- 1982-09-13 SE SE8205200A patent/SE452364B/en not_active IP Right Cessation
- 1982-09-14 DK DK410182A patent/DK153183C/en active
- 1982-09-14 JP JP57159040A patent/JPS58138998A/en active Granted
- 1982-09-14 NO NO823115A patent/NO150820C/en unknown
- 1982-09-14 CH CH5449/82A patent/CH661347A5/en not_active IP Right Cessation
- 1982-09-14 FR FR8215514A patent/FR2521281B1/en not_active Expired
- 1982-09-15 AU AU88433/82A patent/AU530408B2/en not_active Ceased
- 1982-09-15 CA CA000411465A patent/CA1190434A/en not_active Expired
- 1982-09-15 DE DE3234269A patent/DE3234269C2/en not_active Expired
- 1982-09-15 IT IT49119/82A patent/IT1149076B/en active
- 1982-09-15 ES ES515721A patent/ES8308060A1/en not_active Expired
- 1982-09-15 KR KR8204174A patent/KR860000220B1/en active
-
1988
- 1988-05-19 HK HK365/88A patent/HK36588A/en not_active IP Right Cessation
Also Published As
| Publication number | Publication date |
|---|---|
| BE894382A (en) | 1983-03-14 |
| IT1149076B (en) | 1986-12-03 |
| SE452364B (en) | 1987-11-23 |
| ES515721A0 (en) | 1983-08-16 |
| FR2521281A1 (en) | 1983-08-12 |
| IT8249119A0 (en) | 1982-09-15 |
| ES8308060A1 (en) | 1983-08-16 |
| DK410182A (en) | 1983-08-11 |
| NO150820B (en) | 1984-09-10 |
| NO150820C (en) | 1985-01-09 |
| JPS6364720B2 (en) | 1988-12-13 |
| FR2521281B1 (en) | 1986-06-06 |
| NL184340C (en) | 1989-06-16 |
| CH661347A5 (en) | 1987-07-15 |
| DK153183C (en) | 1988-11-14 |
| DK153183B (en) | 1988-06-20 |
| GB2115117A (en) | 1983-09-01 |
| IL66624A (en) | 1986-04-29 |
| AU530408B2 (en) | 1983-07-14 |
| SE8205200D0 (en) | 1982-09-13 |
| JPS58138998A (en) | 1983-08-18 |
| NL184340B (en) | 1989-01-16 |
| DE3234269C2 (en) | 1985-05-09 |
| NL8203531A (en) | 1983-09-01 |
| NO823115L (en) | 1983-08-11 |
| KR840001706A (en) | 1984-05-16 |
| SE8205200L (en) | 1983-08-11 |
| DE3234269A1 (en) | 1983-08-25 |
| HK36588A (en) | 1988-05-27 |
| GB2115117B (en) | 1985-11-06 |
| KR860000220B1 (en) | 1986-03-15 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| MKEC | Expiry (correction) | ||
| MKEX | Expiry |