CA1190433A - Spring-erected telescopic wing support structure - Google Patents
Spring-erected telescopic wing support structureInfo
- Publication number
- CA1190433A CA1190433A CA000411461A CA411461A CA1190433A CA 1190433 A CA1190433 A CA 1190433A CA 000411461 A CA000411461 A CA 000411461A CA 411461 A CA411461 A CA 411461A CA 1190433 A CA1190433 A CA 1190433A
- Authority
- CA
- Canada
- Prior art keywords
- strut
- strut assembly
- struts
- assembly
- base plate
- 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
Abstract
SPRING-ERECTED TELESCOPIC WING SUPPORT STRUCTURE
ABSTRACT OF THE DISCLOSURE
A wing support structure for a self-erecting collapsible wing includes a telescoping strut assembly including a leading strut and a trailing strut each pinned at an inner end to fixed pins on a base support structure and pinned to a common pivot pin at the outer end and each strut being telescoping for retraction to a colinear position and spring biased to an outward fully deployed position. Each strut includes inner and outer tubular strut members in which is confined a compression spring with the inner and outer members including an antirotation lock and an anticollapse lock.
ABSTRACT OF THE DISCLOSURE
A wing support structure for a self-erecting collapsible wing includes a telescoping strut assembly including a leading strut and a trailing strut each pinned at an inner end to fixed pins on a base support structure and pinned to a common pivot pin at the outer end and each strut being telescoping for retraction to a colinear position and spring biased to an outward fully deployed position. Each strut includes inner and outer tubular strut members in which is confined a compression spring with the inner and outer members including an antirotation lock and an anticollapse lock.
Description
--1 =
SPRING-ERECTEI:~ TELESCOPIC ~ING SUPPORT STRUCTURE
~3ACKGRC~ND C)F THE INVENTION
The present invention relates to rockets and missiles S and pertains parti cularly to collapsible wing structures for ~uch missilesu P~any rockets and missiles utiliæe some form of wing or s~abili~er structure ~or s~abili~ing and guiding the mis-sile during flighSq Missiles are fre~quen~ly stored and launched from tubular launchers and ar~3 frequently deployed from a~rcraft or o~her missiles. Ilnder such circumstances ~t is frequently necessary ~o minimize the space for the missile until it is launched. Folding wings of various types and configurations have been utilized in the pas'c to minimize the space required for such missiles The premium Por space requires that the folding or collapsing win~ structures be foldable or coliapsible to a minimum space. In addition, the flight charactertstics of the missile require op'cimum r~liability and per~ormallce of the deployed wing structure. It is therefore deslrable that the folding wing s~ructure have highly efficient fïight characteris'cics and, at the sam~ time, be ~oldable 'co a minimum space.
SUMMARY AND )BJECTS OF THE INVENTION
It is therefore the primary object o~ 'che present invention to provide an improved wing support structure for col 1 aps i bl e wi ngs .
In accordance with the primary aspect of the pres~nt invention, a ~elescopic wing support struc~ure for a collapsible and extensible wing structure ~ncll~de~ lnner ~'~
and outer telescoping ~trut members including a leading trut and a trailing ~trut, ea~h pivoted at an inner end to a fixed hinge pin and including ~ubular telescoping ~nner and outer members with the inner members pinned to a common ~loating hinge pin and being telescspi~a~ly compressed t~
colinear position with coil spring~ disposed within th~
tubular stru~ members for biasing ~he members to ~he fully deployed extended pos tion.
BRIEF DESCRIPTION OF THE DRAWINGS
The above and other ob~ects and adv~ntage~ o~ the presen~ inven~ion will become apparent from the ~ollowing description when read in conjunction with the accompanying drawings wherein:
Figure 1 is a perspective view o a missile ~ncorporating the self-erecting wing structureD
Fig~re 2 is an enlarged side ~levation view of a single erec~ed wing unit.
Figure 3 is a top plan view of the wing unitO
Figure 4 is a sec~ional v~ew taken on line 4~4 o~
Figure 3.
Figure 5 is ~ ~ect;onal view taken on line 5-~ of Figure 3.
~igure 6 i~ sec~ional view, similar ~o Figure 4, but with the wing folded and a retaining cover in place.
Figure 7 is an enlar~ed ~ectional v~ew taken on llne 7-7 of ~igure 2.
~iyure B ~s an enlarged sectional YieW ~aken on line 8-8 of Figure 20 Figure 9 i5 an enlarged ~ectional view ~aken on line 9-9 of ~igure 6~
~ igure 10 i~ a per~pective ~iew o~ ~he wing stru~
~oint and alignment mean~
Figure 11 is a perspectiYe view of one wing strut lock arrangementO
DETAILED DESCRXPTIO~ OF A PREFERRED E~BODIMENT
~ urning to ~he drawings, ther~ is lllustrated in Fi~ure 1 a missile ha~ing a ~enerally cylindrlcal body 10 with a nose cone 12 and a plural~ty of radially outwardly extending win~s 14 extending outwardly from a plurality o circumf~rentially arranged longitudinally extending ~lot~
16 in ~he body 10. ~ plurality of ~uiding or steerin~ fins or rudders 18 extend radially outward ~rom the tail end of the missile bodyO
The missile can have any suitable form o guidance and lS propulsion systems and any required configuration o~
warhead, The missile can be launched in any ~uitable manner such as from ~r~und vehicles or locations~ aircxaft, or other missile~O The Gpace ~aving developments of the present invention, however, were primarily developed for utiliza~ion in missiles ~ranspor~ed by other missile~
wherein ~pace and reliability is a premium.
The wings can have any su~able configura~ion wi~h the illustrated embodiment having a generally triangular configuration. The wing i~ constructed of a flexible or
SPRING-ERECTEI:~ TELESCOPIC ~ING SUPPORT STRUCTURE
~3ACKGRC~ND C)F THE INVENTION
The present invention relates to rockets and missiles S and pertains parti cularly to collapsible wing structures for ~uch missilesu P~any rockets and missiles utiliæe some form of wing or s~abili~er structure ~or s~abili~ing and guiding the mis-sile during flighSq Missiles are fre~quen~ly stored and launched from tubular launchers and ar~3 frequently deployed from a~rcraft or o~her missiles. Ilnder such circumstances ~t is frequently necessary ~o minimize the space for the missile until it is launched. Folding wings of various types and configurations have been utilized in the pas'c to minimize the space required for such missiles The premium Por space requires that the folding or collapsing win~ structures be foldable or coliapsible to a minimum space. In addition, the flight charactertstics of the missile require op'cimum r~liability and per~ormallce of the deployed wing structure. It is therefore deslrable that the folding wing s~ructure have highly efficient fïight characteris'cics and, at the sam~ time, be ~oldable 'co a minimum space.
SUMMARY AND )BJECTS OF THE INVENTION
It is therefore the primary object o~ 'che present invention to provide an improved wing support structure for col 1 aps i bl e wi ngs .
In accordance with the primary aspect of the pres~nt invention, a ~elescopic wing support struc~ure for a collapsible and extensible wing structure ~ncll~de~ lnner ~'~
and outer telescoping ~trut members including a leading trut and a trailing ~trut, ea~h pivoted at an inner end to a fixed hinge pin and including ~ubular telescoping ~nner and outer members with the inner members pinned to a common ~loating hinge pin and being telescspi~a~ly compressed t~
colinear position with coil spring~ disposed within th~
tubular stru~ members for biasing ~he members to ~he fully deployed extended pos tion.
BRIEF DESCRIPTION OF THE DRAWINGS
The above and other ob~ects and adv~ntage~ o~ the presen~ inven~ion will become apparent from the ~ollowing description when read in conjunction with the accompanying drawings wherein:
Figure 1 is a perspective view o a missile ~ncorporating the self-erecting wing structureD
Fig~re 2 is an enlarged side ~levation view of a single erec~ed wing unit.
Figure 3 is a top plan view of the wing unitO
Figure 4 is a sec~ional v~ew taken on line 4~4 o~
Figure 3.
Figure 5 is ~ ~ect;onal view taken on line 5-~ of Figure 3.
~igure 6 i~ sec~ional view, similar ~o Figure 4, but with the wing folded and a retaining cover in place.
Figure 7 is an enlar~ed ~ectional v~ew taken on llne 7-7 of ~igure 2.
~iyure B ~s an enlarged sectional YieW ~aken on line 8-8 of Figure 20 Figure 9 i5 an enlarged ~ectional view ~aken on line 9-9 of ~igure 6~
~ igure 10 i~ a per~pective ~iew o~ ~he wing stru~
~oint and alignment mean~
Figure 11 is a perspectiYe view of one wing strut lock arrangementO
DETAILED DESCRXPTIO~ OF A PREFERRED E~BODIMENT
~ urning to ~he drawings, ther~ is lllustrated in Fi~ure 1 a missile ha~ing a ~enerally cylindrlcal body 10 with a nose cone 12 and a plural~ty of radially outwardly extending win~s 14 extending outwardly from a plurality o circumf~rentially arranged longitudinally extending ~lot~
16 in ~he body 10. ~ plurality of ~uiding or steerin~ fins or rudders 18 extend radially outward ~rom the tail end of the missile bodyO
The missile can have any suitable form o guidance and lS propulsion systems and any required configuration o~
warhead, The missile can be launched in any ~uitable manner such as from ~r~und vehicles or locations~ aircxaft, or other missile~O The Gpace ~aving developments of the present invention, however, were primarily developed for utiliza~ion in missiles ~ranspor~ed by other missile~
wherein ~pace and reliability is a premium.
The wings can have any su~able configura~ion wi~h the illustrated embodiment having a generally triangular configuration. The wing i~ constructed of a flexible or
2~ pliable ma~erial such as a llghtweigh~ nylon or dacron and i~ out and sewn in a way ~hat it precisely conforms to the supportin~ strut assembly in its extended position.
The wing ~ssembly i~ ~elf-contained and ls a completely operable modular unit that can be d~tachably mounted within the rocket body posi~ionea or extenslon or ,, retraction of the wing through a slot in the rocket body.
The wing ass~mbly includes a channel housin~ 2D having an elongated multiwidth slot 22 extending the length of the hou~in~. The housin~ 20 ~as an ou~er coniguration 5 eonformirlg substantially ~o the sha~e of the ~urface o the mis~le ~nd inclu~es means tha~ wlll be de~cribed~
including a disposable c~ver for covering ~he retracted wing opening. The housing body 20 includes a base plate 24 ~s can be~t be ~een in Figures 7 through 9. The bas~ plate 2~ is detach2ble fÆom the housing 20 and ~erves as the primary attachment ~tructure for tbe wing struts~ The base plate 24 also clamps the wing covering fabric 5between the base plate and housing.
The housing is of a dep'ch and width to receive and 15 enclose the collapsed wing strut assembly and the fabric covering thereof and includes a detachable cover 26 as shown in Figure 9 for coverirlg !the retrac~ed wing pocke~O
The support ~trut ~ssembly for the wing fabric iL~ est seen in Figure 4 arld includes a f orward strut assembly pivo~ally mounted or hinged on a forward hinge bracket 28 mounted lto the forward end of the bottom plate 24 and a ~.railing stru'c pivotally mounted ~eo a trailing hia~ge bracket 30 secured to the bo~tom plate 24. The forward ~trut includes a lower outer tubular strut member 32 pivotally mounted or hinged to the bracket 28 and telescopingly receiving an inner tubular strut member 34 which is pivotally secured by means of a hinge pin 36 at the outer end to the trailing strutJ A compres~ion sprlng 38 is mounted within the bore of both the lower and upper ~ubular members 32 ~nd 34 and extends ~ubsta~ially ~he ~ 33 --S--full length thereof. ~his ~pring is preferably under ~ufficient compression at its ~utermost position to retain ~he strut in its extended position under normal circums~anoes~
5The ~ra~ling stru~ i5 substantially identical to the leading strut including a lower ~ubular ~rut m~mber 40 hinged to the hinge bracket 30 and telescopingly receiv~ng a ~ubular inner or upper tubular strut member 42~ A
compression ~pring 44 i~ con~ined within ~he bore of the 10tubular ~embers and extends substantially the ~ull length thereof and ~imllarly is under compression at ~ts ou~ermost position for retaining ~he strut in i~s extended position.
Turning to Figure 10, the ou~er end of inner strut member 34 includes a bi~urca~ed binye bracket member 46 15receiving a hinge member 48 of the inner strut member 42.
Each ~trut is provided with an extension or anticollapse lock to prevent the wins lo~ding from compress;ng the strut. The5e loc~s are formed a~ tabs 50 and S2 on the inner struts 34 ~nd 4~, respe~tively. This 20~trut lock as best ehown in detail in Figure 1~, actually consists of a small finger or tab ~ormed by cu~ting a n~rrow U-shaped slot in the wall of the upper strut mem ber~ ~he finger so formed is bent or forced outward with i~s free end point.ing toward the open end o~ the upper 15~rut 34 or 42 such tha~ when biased outward it engages ~he outer end o the oute.r strut member 32 or 40. ~he free end is ben outward and twisted sll~htly, approxima~ely 10~ and ~pecifically located above the outer ~nd o the lower ~trut when the wing i~ in i~s erected position. The stru~ lock 30ls preferably located on the unders~de of the fitrUt member away from the fabric coverin~ 'co prevent or avoid damage thereto, but ls positioned to be squee~ed or` pressed by the finger to the disengaged posi'cion below the inside diameter of the lower ~tru~ member to permi~ intentional collapse of 5 the stru~. , At leas~c one of the struts ~hould be provided with an antirotation lock to prevent acciden~al rotation of the outer ~rut member~ when l:he ~trut~ are in a colinear or collapsed position~, Turnîng to ~igures fi and la, lû an~lrotation l~cks are provided and each respectively consists of pins 54 and 56 extending outward from the upper ~trut member at a position to engage ~lots 58 and 60 at ~he outer end of 'che ïower ~trut members 32 and 40 upon complete collapse of the strut assembly to the colinear 15 position as shown in Figures 6 and 10. ~lthough wo locks are illustrated, one iEor each ~trut, a single lock would appear to ~erve the purpose iA mos~ instances.
Turning now to Figure 4, ~ leaf ~pring 62 is disposed or mounted on the base plate 24 disposed directly beneath 20 ~he strut assembly for engaging and applying a force to the s'crut assembly below the hinge pin 36 ~pon folding of the ~truts to the collapsed position as shown In Figuze 6.
This spring 62 provides an initial outward thrl~st or force on the ~truts preventing ~hem :from lockillg in the collapsed 25 position.
The fabric cover 66 of 'che wing, as previously discussed~ is ~haped ~o encompass the strut s~ructure and inc~udes a base por~ion or skirt portion 67 tha~ ~s secured to the wing housing 20 by clamping between the base plate 30 24 and the housing and including periphera~ clamp pla~es 64
The wing ~ssembly i~ ~elf-contained and ls a completely operable modular unit that can be d~tachably mounted within the rocket body posi~ionea or extenslon or ,, retraction of the wing through a slot in the rocket body.
The wing ass~mbly includes a channel housin~ 2D having an elongated multiwidth slot 22 extending the length of the hou~in~. The housin~ 20 ~as an ou~er coniguration 5 eonformirlg substantially ~o the sha~e of the ~urface o the mis~le ~nd inclu~es means tha~ wlll be de~cribed~
including a disposable c~ver for covering ~he retracted wing opening. The housing body 20 includes a base plate 24 ~s can be~t be ~een in Figures 7 through 9. The bas~ plate 2~ is detach2ble fÆom the housing 20 and ~erves as the primary attachment ~tructure for tbe wing struts~ The base plate 24 also clamps the wing covering fabric 5between the base plate and housing.
The housing is of a dep'ch and width to receive and 15 enclose the collapsed wing strut assembly and the fabric covering thereof and includes a detachable cover 26 as shown in Figure 9 for coverirlg !the retrac~ed wing pocke~O
The support ~trut ~ssembly for the wing fabric iL~ est seen in Figure 4 arld includes a f orward strut assembly pivo~ally mounted or hinged on a forward hinge bracket 28 mounted lto the forward end of the bottom plate 24 and a ~.railing stru'c pivotally mounted ~eo a trailing hia~ge bracket 30 secured to the bo~tom plate 24. The forward ~trut includes a lower outer tubular strut member 32 pivotally mounted or hinged to the bracket 28 and telescopingly receiving an inner tubular strut member 34 which is pivotally secured by means of a hinge pin 36 at the outer end to the trailing strutJ A compres~ion sprlng 38 is mounted within the bore of both the lower and upper ~ubular members 32 ~nd 34 and extends ~ubsta~ially ~he ~ 33 --S--full length thereof. ~his ~pring is preferably under ~ufficient compression at its ~utermost position to retain ~he strut in its extended position under normal circums~anoes~
5The ~ra~ling stru~ i5 substantially identical to the leading strut including a lower ~ubular ~rut m~mber 40 hinged to the hinge bracket 30 and telescopingly receiv~ng a ~ubular inner or upper tubular strut member 42~ A
compression ~pring 44 i~ con~ined within ~he bore of the 10tubular ~embers and extends substantially the ~ull length thereof and ~imllarly is under compression at ~ts ou~ermost position for retaining ~he strut in i~s extended position.
Turning to Figure 10, the ou~er end of inner strut member 34 includes a bi~urca~ed binye bracket member 46 15receiving a hinge member 48 of the inner strut member 42.
Each ~trut is provided with an extension or anticollapse lock to prevent the wins lo~ding from compress;ng the strut. The5e loc~s are formed a~ tabs 50 and S2 on the inner struts 34 ~nd 4~, respe~tively. This 20~trut lock as best ehown in detail in Figure 1~, actually consists of a small finger or tab ~ormed by cu~ting a n~rrow U-shaped slot in the wall of the upper strut mem ber~ ~he finger so formed is bent or forced outward with i~s free end point.ing toward the open end o~ the upper 15~rut 34 or 42 such tha~ when biased outward it engages ~he outer end o the oute.r strut member 32 or 40. ~he free end is ben outward and twisted sll~htly, approxima~ely 10~ and ~pecifically located above the outer ~nd o the lower ~trut when the wing i~ in i~s erected position. The stru~ lock 30ls preferably located on the unders~de of the fitrUt member away from the fabric coverin~ 'co prevent or avoid damage thereto, but ls positioned to be squee~ed or` pressed by the finger to the disengaged posi'cion below the inside diameter of the lower ~tru~ member to permi~ intentional collapse of 5 the stru~. , At leas~c one of the struts ~hould be provided with an antirotation lock to prevent acciden~al rotation of the outer ~rut member~ when l:he ~trut~ are in a colinear or collapsed position~, Turnîng to ~igures fi and la, lû an~lrotation l~cks are provided and each respectively consists of pins 54 and 56 extending outward from the upper ~trut member at a position to engage ~lots 58 and 60 at ~he outer end of 'che ïower ~trut members 32 and 40 upon complete collapse of the strut assembly to the colinear 15 position as shown in Figures 6 and 10. ~lthough wo locks are illustrated, one iEor each ~trut, a single lock would appear to ~erve the purpose iA mos~ instances.
Turning now to Figure 4, ~ leaf ~pring 62 is disposed or mounted on the base plate 24 disposed directly beneath 20 ~he strut assembly for engaging and applying a force to the s'crut assembly below the hinge pin 36 ~pon folding of the ~truts to the collapsed position as shown In Figuze 6.
This spring 62 provides an initial outward thrl~st or force on the ~truts preventing ~hem :from lockillg in the collapsed 25 position.
The fabric cover 66 of 'che wing, as previously discussed~ is ~haped ~o encompass the strut s~ructure and inc~udes a base por~ion or skirt portion 67 tha~ ~s secured to the wing housing 20 by clamping between the base plate 30 24 and the housing and including periphera~ clamp pla~es 64
3~
Z15 can be seen in Figures 8 and 9O These ensure a secure attachment of the wing fabr~c ~o ~he wing ~tructure.
The above described wing csn be collapsed in~co a ~olded position and rolled w~thin the wing housing as ~hown S in Figure 9. This is accompllshed by compressin~ the ~trut ~ocks ~nd applying a force at the ~cip of the win~ ~n a direction ltha~c telescop~cally compresses or collapses the two struts. The strut5 become progressively ~horter and E~ivot al:out the lower h~nge p~s~s untll they reach the fully 10 folded or c:ollapsed posi~ion where they are collnear and lylng against the base pla~e 24 as ~hown in Figures 6 and 9~. A this point, the compress~on springs 38 and 44 within the two struts ar,e fully compressed to very near the;r solid i-eights at which position they deliver the~ r ~5 maximum force. ~ith the struts ~n this position~ however, the spring force i~ in a direc~ion colinear or coaxlally thereof ~nd does not tend to f orce the wings open. In order to initiate unfolding of the wings, ~ t ls necessary to bias or force the ~trut fxom this position. This 1~
20 accompli~hed by means of the lea spring 62 ~pplying a force biasing the struts a small distance outward such that the compression ~prings wil:hin the ~truts act to quickly ~nap the wing vu~cward ~o ilts fully e~s~cended posi~ion. The ~pring 6~ is posi~ioned and shaped, as ~hown ~n lFigure 4, 25 such tha~: wherl the s ruts ar~ in a fully collapsed posi~on as ~hown in Figure 6 the spring is loaded to provlde a initial force for extension o the ~crut~ and &~lng ass embly .
A releasable wing cover 26 l~ adapted to extend over ~nd cover the folded wing structure ~s best ~een9 f or 3;~
example, in ~i~ures 6 and 9. The wing cover 26 comprises ~n elongated qenerally rectangular plate covering the hous-lng opening when the wing ~s folded thereinO The wirlg cover 26 as best ~een ~n Figuxe 9 includes- a plurallty of 5 hinge tabs ~8 on one side or ex~cending along one side of the cover and a plurality of latch t~bs 70 extend~ng along the other ~ide of the cover. The upper surface of ~he cover as ~een in Figure 9 is curved to conform generally ~o the confiquration of ~he missile hou~ing to provide m~nl-10 mum resistance to airflow ~nd to eliminate space occupylngpro~ruberances. As best ~een in ~igure 3, a plurality of hinge pin~ 7.2 are D~ounted in a plurali~y of ~lot~ or depressions 74 along one side o~ the wing housing.
~ lideable latch plate 76 as shown in Figure 5 i~ secured by 15 means of a plurality of slo~cs 7B and sho~lder screws 79 o the side wall of the hous~ng with a plurality o~ latch fingers 80 biased So a po~ition o~rerlapping a plurality of ta~:? receiving filotE 82 in ~he sidewall of the housin~O ~he latch plate is biased ~y means of a compression spring 84 20 at one end of the plate and housing. A plunger 86 within a cylinder 87 engagin~ the end of the latch plate is provided with a small explosive char~e 88 within a chamber which is ignited to ~hift the latch plate to the released posit:l on for rel ease of the cover. Release of the cover permits the 25 strut assembly ~o ex~endr ~orcing ~he cover ou~wardsO The cover is then swep~c away by ~irflow along the misslle body., The wing is then free ta snap out 9:o its fully deployed posi tion.
_g_ While we have illustrated and descrlbed our lnvention by means o~ specific embodim~nts, it ~5 ~0 be unders'cood that numerous changes and modificat~on~ may be made therein without departing from the spirit and scope of the 5 invention as def ined in 'che apEended cïaimsO
Z15 can be seen in Figures 8 and 9O These ensure a secure attachment of the wing fabr~c ~o ~he wing ~tructure.
The above described wing csn be collapsed in~co a ~olded position and rolled w~thin the wing housing as ~hown S in Figure 9. This is accompllshed by compressin~ the ~trut ~ocks ~nd applying a force at the ~cip of the win~ ~n a direction ltha~c telescop~cally compresses or collapses the two struts. The strut5 become progressively ~horter and E~ivot al:out the lower h~nge p~s~s untll they reach the fully 10 folded or c:ollapsed posi~ion where they are collnear and lylng against the base pla~e 24 as ~hown in Figures 6 and 9~. A this point, the compress~on springs 38 and 44 within the two struts ar,e fully compressed to very near the;r solid i-eights at which position they deliver the~ r ~5 maximum force. ~ith the struts ~n this position~ however, the spring force i~ in a direc~ion colinear or coaxlally thereof ~nd does not tend to f orce the wings open. In order to initiate unfolding of the wings, ~ t ls necessary to bias or force the ~trut fxom this position. This 1~
20 accompli~hed by means of the lea spring 62 ~pplying a force biasing the struts a small distance outward such that the compression ~prings wil:hin the ~truts act to quickly ~nap the wing vu~cward ~o ilts fully e~s~cended posi~ion. The ~pring 6~ is posi~ioned and shaped, as ~hown ~n lFigure 4, 25 such tha~: wherl the s ruts ar~ in a fully collapsed posi~on as ~hown in Figure 6 the spring is loaded to provlde a initial force for extension o the ~crut~ and &~lng ass embly .
A releasable wing cover 26 l~ adapted to extend over ~nd cover the folded wing structure ~s best ~een9 f or 3;~
example, in ~i~ures 6 and 9. The wing cover 26 comprises ~n elongated qenerally rectangular plate covering the hous-lng opening when the wing ~s folded thereinO The wirlg cover 26 as best ~een ~n Figuxe 9 includes- a plurallty of 5 hinge tabs ~8 on one side or ex~cending along one side of the cover and a plurality of latch t~bs 70 extend~ng along the other ~ide of the cover. The upper surface of ~he cover as ~een in Figure 9 is curved to conform generally ~o the confiquration of ~he missile hou~ing to provide m~nl-10 mum resistance to airflow ~nd to eliminate space occupylngpro~ruberances. As best ~een in ~igure 3, a plurality of hinge pin~ 7.2 are D~ounted in a plurali~y of ~lot~ or depressions 74 along one side o~ the wing housing.
~ lideable latch plate 76 as shown in Figure 5 i~ secured by 15 means of a plurality of slo~cs 7B and sho~lder screws 79 o the side wall of the hous~ng with a plurality o~ latch fingers 80 biased So a po~ition o~rerlapping a plurality of ta~:? receiving filotE 82 in ~he sidewall of the housin~O ~he latch plate is biased ~y means of a compression spring 84 20 at one end of the plate and housing. A plunger 86 within a cylinder 87 engagin~ the end of the latch plate is provided with a small explosive char~e 88 within a chamber which is ignited to ~hift the latch plate to the released posit:l on for rel ease of the cover. Release of the cover permits the 25 strut assembly ~o ex~endr ~orcing ~he cover ou~wardsO The cover is then swep~c away by ~irflow along the misslle body., The wing is then free ta snap out 9:o its fully deployed posi tion.
_g_ While we have illustrated and descrlbed our lnvention by means o~ specific embodim~nts, it ~5 ~0 be unders'cood that numerous changes and modificat~on~ may be made therein without departing from the spirit and scope of the 5 invention as def ined in 'che apEended cïaimsO
Claims (20)
PROPERTY OR PRIVILEGE IS CLAIMED ARE DEFINED AS FOLLOWS:
1. An extensible strut assembly for a self-erecting wing, said strut assembly comprising:
a leading strut and a trailing strut, each strut comprising a lower telescoping tubular member pivotally mounted at the lower end on a fixed hinge pin, and an upper telescoping tubular member telescopi-cally mounted in said lower tubular member and pivotally connected to a common hinge pin, and, a compression spring disposed within the lower and upper telescoping strut member of each strut.
a leading strut and a trailing strut, each strut comprising a lower telescoping tubular member pivotally mounted at the lower end on a fixed hinge pin, and an upper telescoping tubular member telescopi-cally mounted in said lower tubular member and pivotally connected to a common hinge pin, and, a compression spring disposed within the lower and upper telescoping strut member of each strut.
2. The strut assembly of claim 1 including an alignment pin and slot on at least one of said struts for maintaining alignment of said struts.
3. The strut assembly of claim 2, wherein said compression spring is substantially bottomed when said struts are collapsed to a colinear position.
4. The strut assembly of claim 3, wherein at least one of said leading strut and said trailing strut includes locking means for locking said strut in the extended position.
5. The strut assembly of claim 4, including a base plate, and said fixed hinge pins are fixed to said plate.
6. The strut assembly of claim 5, including spring means mounted on said base plate for engaging said strut assembly in the retracted position for biasing same toward the extended position.
7. The strut assembly of claim 5, wherein said struts are mounted within a double walled flexible wing body.
8. The strut assembly of claim 7, including an elongated housing having walls defining an elongated chamber, said base plate defining the bottom of said housing, and said struts are mounted on said plate and positioned for collapsing to a position totally within said chamber, and detachable cover means covering said chamber for retaining said struts in a collapsed posit-ion within said housing.
9. The strut assembly of claim 8, including releasable latching means for retaining said cover on said housing.
10. The strut assembly of claim 9, including spring means mounted on said base plate for engaging and biasing said struts from the colinear position when said cover is released.
11. An extensible strut assembly for a self-erecting wing, said strut assembly comprising:
a leading strut and a trailing strut, each strut comprising a lower telescoping tubular member pivotally mounted at the lower end on a fixed hinge pin, and an upper telescoping tubular member telescopi-cally mounted in said lower tubular member and pivotal-ly connected to a common hinge pin, said struts being collapsible to a colinear position and extendable outwardly to a fully deployed position;
a compression spring disposed within the lower and upper telescoping strut member of each strut wherein said compression spring is substantially bottomed when said struts are collapsed to the colinear position;
an anti-rotation alignment pin and slot on at least one of said struts for maintaining alignment of said struts about the axis thereof when in the colinear position; and at least one of said leading strut and said trailing strut includes locking means for locking said strut in the extended position.
a leading strut and a trailing strut, each strut comprising a lower telescoping tubular member pivotally mounted at the lower end on a fixed hinge pin, and an upper telescoping tubular member telescopi-cally mounted in said lower tubular member and pivotal-ly connected to a common hinge pin, said struts being collapsible to a colinear position and extendable outwardly to a fully deployed position;
a compression spring disposed within the lower and upper telescoping strut member of each strut wherein said compression spring is substantially bottomed when said struts are collapsed to the colinear position;
an anti-rotation alignment pin and slot on at least one of said struts for maintaining alignment of said struts about the axis thereof when in the colinear position; and at least one of said leading strut and said trailing strut includes locking means for locking said strut in the extended position.
12. The strut assembly of claim 11, including a base plate, and said fixed hinge pins are fixed to said plate.
13. The strut assembly of claim 12, including spring means mounted on said base plate between said fixed hinge pins for engaging said strut assembly in the retracted position for biasing same toward the extended position.
14. The strut assembly of claim 13, wherein said struts are mounted within a double walled flexible wing body.
15. The strut assembly of claim 12, including an elongated housing having walls defining an elongated chamber, said base plate defining the bottom of said housing, and said struts are mounted on said plate and positioned for collapsing to a position totally within said chamber; and detachable cover means covering said chamber for retaining said struts in a collapsed position within said housing.
16. The strut assembly of claim 15, including releasable latching means for retaining said cover on said housing.
17. The strut assembly of claim 16, including spring means mounted on said base plate for engaging and biasing said struts from the colinear position when said cover is released.
18. The strut assembly of claim 13, wherein said spring means comprises a curved leaf spring attached at one end to said base plate and curved outward therefrom.
-12-.
-12-.
19. The strut assembly of claim 11, wherein said slot is formed in the outer end of said lower telescoping member and said pin is mounted on and extends outward from said upper telescoping tubular member.
20. The strut assembly of claim 11, wherein said locking means comprises a biased tab formed in the wall of the upper strut for engaging the end of the lower strut when in the fully deployed position.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US347,396 | 1982-02-10 | ||
| US06/347,396 US4586680A (en) | 1982-02-10 | 1982-02-10 | Spring-erected telescopic wing support structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1190433A true CA1190433A (en) | 1985-07-16 |
Family
ID=23363539
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA000411461A Expired CA1190433A (en) | 1982-02-10 | 1982-09-15 | Spring-erected telescopic wing support structure |
Country Status (19)
| Country | Link |
|---|---|
| US (1) | US4586680A (en) |
| JP (1) | JPS58138999A (en) |
| KR (1) | KR860001011B1 (en) |
| AU (1) | AU530407B2 (en) |
| BE (1) | BE894381A (en) |
| CA (1) | CA1190433A (en) |
| CH (1) | CH660418A5 (en) |
| DE (1) | DE3234267C2 (en) |
| DK (1) | DK154105C (en) |
| ES (1) | ES8308059A1 (en) |
| FR (1) | FR2521280B1 (en) |
| GB (1) | GB2115116B (en) |
| HK (1) | HK92686A (en) |
| IL (1) | IL66623A (en) |
| IT (1) | IT1149075B (en) |
| NL (1) | NL184383C (en) |
| NO (1) | NO152064C (en) |
| SE (1) | SE452363B (en) |
| SG (1) | SG70486G (en) |
Families Citing this family (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2205798B (en) * | 1983-08-11 | 1989-06-01 | Secr Defence | Improvements in or relating to unmanned aircraft. |
| DE3403573A1 (en) * | 1983-11-09 | 1985-08-08 | Diehl GmbH & Co, 8500 Nürnberg | BULLET WITH FOLD-OUT WINGS |
| US4858851A (en) * | 1988-06-07 | 1989-08-22 | General Dynamics Pomona Division | Folding wing structure for missile |
| GB8815060D0 (en) * | 1988-06-24 | 1988-11-16 | British Aerospace | Fin assembly for projectile |
| DE3838738A1 (en) * | 1988-11-15 | 1990-05-23 | Diehl Gmbh & Co | PROJECTILE WITH FOLD-OUT WINGS |
| DE3918244A1 (en) * | 1989-06-05 | 1990-12-06 | Diehl Gmbh & Co | FOLDING WING FROM A MISSILE |
| KR0176320B1 (en) * | 1995-12-09 | 1999-04-01 | 배문한 | Guided missile wing deployment and fixture |
| US5939665A (en) * | 1996-02-12 | 1999-08-17 | The United States Of America As Represented By The Secretary Of The Navy | Brisk maneuvering device for undersea vehicles |
| US7732741B1 (en) | 2006-08-31 | 2010-06-08 | The United States Of America As Represented By The Secretary Of The Navy | Folding articulating wing mechanism |
| US7829830B1 (en) * | 2007-10-19 | 2010-11-09 | Woodward Hrt, Inc. | Techniques for controlling access through a slot on a projectile |
| US8282065B1 (en) * | 2011-07-07 | 2012-10-09 | Myron Stone | Compact, collapsible, self-erecting stand and method of making |
| US9677861B2 (en) * | 2015-04-30 | 2017-06-13 | Raytheon Company | Flechette weapon system and method employing minimal energetic material |
| US10151568B2 (en) * | 2016-03-15 | 2018-12-11 | The Boeing Company | Guided projectile and method of enabling guidance thereof |
| US20210094672A1 (en) * | 2018-05-08 | 2021-04-01 | Shivanand SHARMA | Collapsible stabilizer assembly for an aircraft |
| CN112343962B (en) * | 2020-11-03 | 2022-08-19 | 西安航天动力技术研究所 | Damping support of rocket launcher |
Family Cites Families (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA788868A (en) * | 1968-07-02 | Schwesig Reinhold | Tail unit for rockets | |
| FR776253A (en) * | 1933-10-10 | 1935-01-22 | Stopper for telescopic legs for cameras and other applications | |
| US2365577A (en) * | 1943-08-26 | 1944-12-19 | Stephen A Moore | Projectile |
| DE1203647B (en) * | 1962-09-11 | 1965-10-21 | Dynamit Nobel Ag | Fin tail, especially for rocket projectiles |
| DE1199644B (en) * | 1964-04-23 | 1965-08-26 | Iwan Jlieff Dr | Dispensing valve with measuring cup for bottles |
| GB1166489A (en) * | 1965-11-04 | 1969-10-08 | Yoshimi Yazaki | Building Constructions Capable of being Readily Fabricated or Dismantled |
| US4072107A (en) * | 1967-06-07 | 1978-02-07 | The United States Of America As Represented By The Secretary Of The Army | Missile control means |
| US3826448A (en) * | 1972-09-14 | 1974-07-30 | Nasa | Deployable flexible ventral fins for use as an emergency spin-recovery device in aircraft |
| US4351499A (en) * | 1979-09-24 | 1982-09-28 | General Dynamics | Double fabric, retractable, self-erecting wing for missle |
-
1982
- 1982-02-10 US US06/347,396 patent/US4586680A/en not_active Expired - Lifetime
- 1982-02-10 KR KR8204173A patent/KR860001011B1/en active
- 1982-08-23 IL IL66623A patent/IL66623A/en not_active IP Right Cessation
- 1982-09-02 GB GB08225046A patent/GB2115116B/en not_active Expired
- 1982-09-10 NL NLAANVRAGE8203533,A patent/NL184383C/en not_active IP Right Cessation
- 1982-09-13 SE SE8205199A patent/SE452363B/en not_active IP Right Cessation
- 1982-09-13 BE BE0/209000A patent/BE894381A/en not_active IP Right Cessation
- 1982-09-14 JP JP57159042A patent/JPS58138999A/en active Granted
- 1982-09-14 CH CH5448/82A patent/CH660418A5/en not_active IP Right Cessation
- 1982-09-14 FR FR8215513A patent/FR2521280B1/en not_active Expired
- 1982-09-14 NO NO823114A patent/NO152064C/en unknown
- 1982-09-14 DK DK410082A patent/DK154105C/en not_active IP Right Cessation
- 1982-09-15 DE DE3234267A patent/DE3234267C2/en not_active Expired
- 1982-09-15 IT IT49118/82A patent/IT1149075B/en active
- 1982-09-15 CA CA000411461A patent/CA1190433A/en not_active Expired
- 1982-09-15 ES ES515720A patent/ES8308059A1/en not_active Expired
- 1982-09-18 AU AU88431/82A patent/AU530407B2/en not_active Ceased
-
1986
- 1986-08-29 SG SG704/86A patent/SG70486G/en unknown
- 1986-12-04 HK HK926/86A patent/HK92686A/en not_active IP Right Cessation
Also Published As
| Publication number | Publication date |
|---|---|
| FR2521280A1 (en) | 1983-08-12 |
| IT1149075B (en) | 1986-12-03 |
| DE3234267C2 (en) | 1985-06-13 |
| CH660418A5 (en) | 1987-04-15 |
| NO152064B (en) | 1985-04-15 |
| NL184383C (en) | 1989-07-03 |
| JPS58138999A (en) | 1983-08-18 |
| FR2521280B1 (en) | 1986-06-06 |
| SE8205199D0 (en) | 1982-09-13 |
| DK154105B (en) | 1988-10-10 |
| NL8203533A (en) | 1983-09-01 |
| AU530407B2 (en) | 1983-07-14 |
| US4586680A (en) | 1986-05-06 |
| IT8249118A0 (en) | 1982-09-15 |
| KR860001011B1 (en) | 1986-07-26 |
| BE894381A (en) | 1983-03-14 |
| SE452363B (en) | 1987-11-23 |
| DK154105C (en) | 1989-03-20 |
| GB2115116B (en) | 1986-07-02 |
| SG70486G (en) | 1987-02-27 |
| NO152064C (en) | 1985-07-24 |
| KR840001705A (en) | 1984-05-16 |
| GB2115116A (en) | 1983-09-01 |
| ES515720A0 (en) | 1983-08-16 |
| NL184383B (en) | 1989-02-01 |
| IL66623A (en) | 1986-04-29 |
| ES8308059A1 (en) | 1983-08-16 |
| SE8205199L (en) | 1983-08-11 |
| DE3234267A1 (en) | 1983-08-25 |
| JPS6231277B2 (en) | 1987-07-07 |
| NO823114L (en) | 1983-08-11 |
| DK410082A (en) | 1983-08-11 |
| HK92686A (en) | 1986-12-12 |
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Legal Events
| Date | Code | Title | Description |
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| MKEC | Expiry (correction) | ||
| MKEX | Expiry |