CA1172479A - Removable external payload carrier for aircraft - Google Patents
Removable external payload carrier for aircraftInfo
- Publication number
- CA1172479A CA1172479A CA000389597A CA389597A CA1172479A CA 1172479 A CA1172479 A CA 1172479A CA 000389597 A CA000389597 A CA 000389597A CA 389597 A CA389597 A CA 389597A CA 1172479 A CA1172479 A CA 1172479A
- Authority
- CA
- Canada
- Prior art keywords
- carrier
- fuselage
- alm
- guide
- payload
- 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
Landscapes
- Automatic Assembly (AREA)
Abstract
REMOVABLE EXTERNAL PAYLOAD
CARRIER FOR AIRCRAFT
ABSTRACT
A carrier including one or more guide tracks, an endless positioning chain associated with each guide track for supporting a payload item, and one or more drive motors for moving the chains in unison with respect to the guide tracks to move a payload item toward an ejection station. A
fairing may be mounted in association with the guide tracks.
The guide tracks encircle the aircraft fuselage and are main-tained under sufficient tension to apply a radial compressive force to the fuselage for securing them thereto. The guide tracks are laterally rigid but are flexible radially to con-form to a range of fuselage contours when subjected to a ten-site force. The guide tracks thus may be secured to different aircraft in order to temporarily transform the aircraft into a military payload carrier, with minimal modification. Follow-ing military employment, the aircraft may be refurbished for non-military usage by removal of the carrier. The carrier is particularly suited for reversibly converting an aircraft to a platform for carrying and launching one or more rockets or cruise missiles.
CARRIER FOR AIRCRAFT
ABSTRACT
A carrier including one or more guide tracks, an endless positioning chain associated with each guide track for supporting a payload item, and one or more drive motors for moving the chains in unison with respect to the guide tracks to move a payload item toward an ejection station. A
fairing may be mounted in association with the guide tracks.
The guide tracks encircle the aircraft fuselage and are main-tained under sufficient tension to apply a radial compressive force to the fuselage for securing them thereto. The guide tracks are laterally rigid but are flexible radially to con-form to a range of fuselage contours when subjected to a ten-site force. The guide tracks thus may be secured to different aircraft in order to temporarily transform the aircraft into a military payload carrier, with minimal modification. Follow-ing military employment, the aircraft may be refurbished for non-military usage by removal of the carrier. The carrier is particularly suited for reversibly converting an aircraft to a platform for carrying and launching one or more rockets or cruise missiles.
Description
.1; L 7 2 4. ~ 9 REIV~)VABLE_EXTE~\IAL P,l\YLOAD
CARRIER FOR AIRCRAFT
BACKG~)UND OF THE II`IVENTI N
~` 5 The present Inventlon relates to payload or stores carrters for attachment to a vehicle. The carrler of thls In-vention Is partlcularly suited for usage with an alrcraft as a carrler of one or more air-launched mlsslles, although ` It may be used with other ml11tary payloads Includlng, but not llmlted to, alr-launched or alr~eJested mtsslles to be used In alr-to-air or air-to-surface combat operatlons, prepackagsd mlsslles in cannlsters for deployment over land or sea arsas, deployable or dlsperslble electronlc counter-measures equ!pment, sensor packages, miniaturlzed pllotless alrcraft, rescue gear, replenlshment supplles, and other loglstlcs support equlpment. It wlll be understood, there-fore, that an aTr-launched mlsslle (ALM) Is dlsclosed her~ln as a partlcular payload t~em for Illustratlve purposes and tha-t thls Inventlon may be used with all other p~yloads and carrler vehlcles not explTcltly mentioned hereln.
The advent of ALM7s has fostered the need for avall~
able aircraft capable of dellverlng one or ~ore ALMIs.
Mllltary atrcraft, of course, offer a nucleus of available ALM carrler vehlcles; however, It would be deslrable ta Increase the number of avallable ALM carrler alrcraft beyond ~; mtlltary aircraft. To thls end, non-mllltary or co~merclal alrcraft have been consldered as posslble ALM carrlers~
provlded that these alrcraft could be temporarlly transformed Into conflguratlons suttable for mTlltary mlsslons. (This temporary transfOrmatlon Is referred to h~relnafter as reverslble oonverston. ) Accordtng to th7s reverslble converslon concept, an alrcraft designed and opera-~ed for commerclal alr transportatlon (passenger, frelght, or combina-tlon) could be used as an ALM carrler wlthout Irreversible modlflcatlon of Its structure, avlonlcs, or other essentlal elements. Llkewlse, a mllltary alrcraft orlglnally not deslgne~ as an ALM carrler (e.g. patrol, survel!lance, transport or tanker alrcraft) could be used for this purpose, agaln without requlrlng Irreverslble modlfTcattons o~ Its structure, avionlcs, or other essenttal elements. Accordlng to " i ~.
further aspects of this concept~ the alrcraft, followlng the i-emporary military use, can be essentlally recovered In Its origlnal conflguratlon without slgnlfTcant refurblshlng~
except for the posslble damage suffered tn the course of milltary operations. Followlng minimal refurblshment, It wlll have the same functlonal performance characterlstlcs as prior to ths military employment period.
ReversTble converslon heretofore has not been practical because the converted alrcraft conflguratlon has been unsatls-factory from -i-he standpolnt of fllght performance obtalned or structural modlfica-tlon requlred. Some converted configura-t70ns typlcally create excesslve drag, or Impose addltional stresses or fatigue on the aircraft above original desi~n ~5 allowables. Other converted configurations require excessiv~
structural modiflcatlon. These converied conflguratlons may be characterlzed as internal carry and external carry.
In the Internal carry conf7guration, It 15 In general requlred to relnforce the floor In which the payload wlll be carrled and to modlfy the cargo doors or other ex1t openlngs through whlch it can ba loaded on the ground and dlscharged In fllght. Misslles preferably should be launched wlth thelr longitudlnal axls along the directlon of fllght. Thls through the currently exlstlng opanlngs in commercial passenger alr-craft Is just about Impossible. Launchlng in other than thlspreferred orTentatlon causes serious stress and fllght dynamic probiems in the Infllght ejectlon operatlon. Relnforcement of the loadlng floor and structural modlficatlons of the launch openlngs are In general expenslve, not only In terms of dlrect cost but also owlng to the duratlon of modiflcations whTch take the airplane out of commerclal serYice with the concomltant loss of revenue. The addltional relnforcement results In permanent payload penalty over extended peace-time periods before the actual milltary use (possibly as long as the operat10nal llfe of the aircraft), the user Is thus forced to suffer the correspondlng revenue loss. Thls Tn turn calls for undeslrable reimbursement vla direct payments or prlvlleges through regulatory declslons.
In the external carry conflguratlon, payload packages
CARRIER FOR AIRCRAFT
BACKG~)UND OF THE II`IVENTI N
~` 5 The present Inventlon relates to payload or stores carrters for attachment to a vehicle. The carrler of thls In-vention Is partlcularly suited for usage with an alrcraft as a carrler of one or more air-launched mlsslles, although ` It may be used with other ml11tary payloads Includlng, but not llmlted to, alr-launched or alr~eJested mtsslles to be used In alr-to-air or air-to-surface combat operatlons, prepackagsd mlsslles in cannlsters for deployment over land or sea arsas, deployable or dlsperslble electronlc counter-measures equ!pment, sensor packages, miniaturlzed pllotless alrcraft, rescue gear, replenlshment supplles, and other loglstlcs support equlpment. It wlll be understood, there-fore, that an aTr-launched mlsslle (ALM) Is dlsclosed her~ln as a partlcular payload t~em for Illustratlve purposes and tha-t thls Inventlon may be used with all other p~yloads and carrler vehlcles not explTcltly mentioned hereln.
The advent of ALM7s has fostered the need for avall~
able aircraft capable of dellverlng one or ~ore ALMIs.
Mllltary atrcraft, of course, offer a nucleus of available ALM carrler vehlcles; however, It would be deslrable ta Increase the number of avallable ALM carrler alrcraft beyond ~; mtlltary aircraft. To thls end, non-mllltary or co~merclal alrcraft have been consldered as posslble ALM carrlers~
provlded that these alrcraft could be temporarlly transformed Into conflguratlons suttable for mTlltary mlsslons. (This temporary transfOrmatlon Is referred to h~relnafter as reverslble oonverston. ) Accordtng to th7s reverslble converslon concept, an alrcraft designed and opera-~ed for commerclal alr transportatlon (passenger, frelght, or combina-tlon) could be used as an ALM carrler wlthout Irreversible modlflcatlon of Its structure, avlonlcs, or other essentlal elements. Llkewlse, a mllltary alrcraft orlglnally not deslgne~ as an ALM carrler (e.g. patrol, survel!lance, transport or tanker alrcraft) could be used for this purpose, agaln without requlrlng Irreverslble modlfTcattons o~ Its structure, avionlcs, or other essenttal elements. Accordlng to " i ~.
further aspects of this concept~ the alrcraft, followlng the i-emporary military use, can be essentlally recovered In Its origlnal conflguratlon without slgnlfTcant refurblshlng~
except for the posslble damage suffered tn the course of milltary operations. Followlng minimal refurblshment, It wlll have the same functlonal performance characterlstlcs as prior to ths military employment period.
ReversTble converslon heretofore has not been practical because the converted alrcraft conflguratlon has been unsatls-factory from -i-he standpolnt of fllght performance obtalned or structural modlfica-tlon requlred. Some converted configura-t70ns typlcally create excesslve drag, or Impose addltional stresses or fatigue on the aircraft above original desi~n ~5 allowables. Other converted configurations require excessiv~
structural modiflcatlon. These converied conflguratlons may be characterlzed as internal carry and external carry.
In the Internal carry conf7guration, It 15 In general requlred to relnforce the floor In which the payload wlll be carrled and to modlfy the cargo doors or other ex1t openlngs through whlch it can ba loaded on the ground and dlscharged In fllght. Misslles preferably should be launched wlth thelr longitudlnal axls along the directlon of fllght. Thls through the currently exlstlng opanlngs in commercial passenger alr-craft Is just about Impossible. Launchlng in other than thlspreferred orTentatlon causes serious stress and fllght dynamic probiems in the Infllght ejectlon operatlon. Relnforcement of the loadlng floor and structural modlficatlons of the launch openlngs are In general expenslve, not only In terms of dlrect cost but also owlng to the duratlon of modiflcations whTch take the airplane out of commerclal serYice with the concomltant loss of revenue. The addltional relnforcement results In permanent payload penalty over extended peace-time periods before the actual milltary use (possibly as long as the operat10nal llfe of the aircraft), the user Is thus forced to suffer the correspondlng revenue loss. Thls Tn turn calls for undeslrable reimbursement vla direct payments or prlvlleges through regulatory declslons.
In the external carry conflguratlon, payload packages
2~7~
such as misslles or cannlsters are attached to the outside of the aircraft, In this instance, of course, drag and aero-elastic stability problems become important conslderatlons. In general, structural modlficattons are requlred to provide the hard point or mounting posts upon which the load can be attached. Drag can be avoTded by provldlng approprlate fairlngs~ but with current destgns tusually referred to as conformal carrlages), such falrtngs must also be attached to the structural strong potnts o~ the aircraft. Once again, structural modlflcatlons to the extent that thoy cause payload panalty and avallabillty loss are - undeslrable as expiained above. Another form of external carry makes use of a rotary rack, such as that used In military alr-craft, mounted in an aerodynamically shaped pod to be carrlsd on a single strong-potnt bullt tn one of the wings of certain commerclal aTrcraft. (The original design purpose of the strong-point was to carry a spare englne). The military payload that can be carried under such condltlons, however9 Is of limited welght.
~O SUMMARY OF THE INVENTION
The present invention provldes a payload carrler for detachable mounting on selected vehtcles havlng bodles whlch are of c~oss-sectlonal outlines within a predetermlned range of , outllnas~ the carrier comprlsfng: guide means engagable wlth the :25 exterior of a vehlcle body about the perlphery thereof; and pay-load posltlonlng means operatively assoclated wlth sald gulde means for movement wiih respect thereto to move a payload article ;~wlth respect to the body perlphery toward a payload eJectlon statlon a~ which the payload article may be released; sald guide means Includtng means conformable to the cross-sectional outllne of the body for applylng a compressive force about the body perlphery to malntaln said guide means In a flxed posltlon thereon.
The present inventlon also provides a method for converiing an alrcraft to an ALM carrler alrcraft, comprlslng the steps of: securlng gulde track means to the alrcraft fuselage about the perlphery thereof essenttally by applytng a peripheral compressive force thereto; and mounting payload posittonlng means to satd gulde meàns for suppor~tng a plura-~' I il r7 2 ~ ~j) 9 --4--lity of ALMIs In parallel alignment with the longitudinal axis of -he fusalage for movement with respect to the fuselage peri-- phery toward an ajectlon station at which an ALM may be releasad, whereby the aircraft may be converted to an ALM carrler and may be refurbished to Its prlor conditlon with essentlally no mod-ificatlon to the fuselage or the structure.
More specifically, the present Inventton provldes a carrier adapted for an external carry configuratlon wherain one or more ALM~s rnay be carrted by an aircraft whlch i5 re-verslbly converted for milTtary usage. As a consequence, any atrcraft of appropriata payload capacity may, using thls inven-tTon, be reversibly converted Into a mllitary payload or ALM
carrier yleldlng acceptable flight parformance, with mlnimal structural modificatton. Followlng military operatlons, the alrcraft may be refurbished for non-milTtary use. Thls Inven-tlon therefore offers to make a natlon s commercial alrllne ~leet, military transport aircraft, and other avallable alrcraft as milltary payload carrters, especlally as ALM carrlers. The Inventlon also offers the posslbillty of convertlng mlll-iary alrcraft, design for other uses, to ALM carrlers, in a reversi-ble modec According to one preferred embodlment of ihe inven-tion, the carrler Includes one or rr,ore conformable guide tracks whlch are secured under tenslon to the a;rcraft fuselage at spaced apart locations along the length thereof. An endless flexlble posltionlng chain Is mounted Inside of each track and Is freely movable about the perlphery of the fuselage Irres-pective of the exact shape of the fuselage In cross-sectlon or of deformatlons therein under flight loads. The positloning chains are motor drlven and so posittonable that payload packages attached thereto can be moved In sequen-iai or arbitrarily chosen ordsr from any inltial posltion along the fuselage perlphery Into the ejection (launch) posltion (s). For ALM applicatton, multlple mlsslles are carrled about the fuselage perlphery In parallel alignment with the longttudlnal axis of the fuselage and are supported at their ends by iwo spaced apart gulde tracks and associated positioning chains. A permanent or jettlson-able fairing surrounds the carrier to ensure relatlvely modest 1 ~72~79 addltlonal drag caus0d by the addltional payload. Excesstve structural loads can be absorbed, if necessary, by Internal braclng of the fuselage. Accordlng to further aspects of the S invention for AUM application in particular, additional ALM s may be carrTed in externally afflxed channels or tracks for reloading. If the slze of the missiles permlt, Internally carried missiles could be loaded into the externai channeis by a transfer device Installed In tha cargo door.
These and other features, obJects, and advantages of ~he present Invention wlll becvme apparent from the detalied description and clalms to follow, taken In conJunction with the accompanying drawings in which lilce parts bear llke reference numerals.
BR_EF DESCRIPTION OF THE DRAWINGS
FIG. I is a perspective of an alrcraft equipped wTth two carrlers according to thls invention, the carriers mounted `- fore and aft of -the wing~
' FIG. 2 is a fragmentary perspectlve of the forward : 20 Flg. I carrler;
FIG. 3 is a perspective of one gulde track section and associated positlonTng chaln of the Flg. 2 carrier;
FIG. 4 Is a perspective of the Flg. 3 gulde track;
FIG. 5 Is a slde elevation of the Fig. 4 guide track;
FIG. 6 is a slde elevation generally stmliar to Fig. S
but ~n expanded scale of one end of the guide track In dlfferent posltlons;
FIG. 7 is a perspectlve of the Fig. I forward carrler wlth a falring and supportlng an ALM payload;
FIG, 8 Is a section talcen along the llna 8-8 in Flg. 7;
FIG. 9 is a sectlon taken along the llne 9-9 In Flg. 8;
FIG. 10 Is a section taken along the llne 10-10 tn Flg. 2;
FIG. Il Is a side elevatlon of a modifled payload suppor~;
FIG. 12 Is an end elevatlon of the Flg. Il support;
FIG. 13 is a side elevatlon of a second mQdlfied payload support;
FIG. 14 Is a perspective generally slmilar to Fig. 7 l 1~2~1'7~
of a modlfied chaln drive assembly9 FIG. 15 Ts a fragmentary perspectlve on enlarged scale of the guide track of the Flg. 14 assembly;
FIG. 16 is a perspectlve generally slmllar to Fig. 1 of an aircraft equlpped wi-th a single carrler ~falring not shown for clari ~) and a reloading assembly;
FIG. 17 is a fragmentary sectlon generally slmllar to Flg, 9 of the forward carrier wilh an expendable falrtng) IO depictlng the fairlng wIth a portlon removed to permit taunch of an ALM.
DE~AILED DESCRIPTiON OF THE DRAW ! NGS
Referrlng to Ftg. I of the drawings, a jet transport aircraft may be eguipped wlth one or more carrters of this ~ 15 invention to reverslbly convert ~hat aircraft Tnto an ALM
;~ carrler. In the example Illustrated In Fig. 1, two carriers 6 and ~ ara detachably mounted on the aircraft fuselage 18 fore and aft of wing 21, respectlvely. Fig~ 16 depici-s a simllar aircraft equipped wtth a slngle forward carrler and a dorsally located reloading assembly, to be descrlbed presently. The Flg. I carrlers 6 and 8 are essentlally Identlcal and therefore only carrler 6 Is described In detall herelnafter.
~ aferrfng now to Flgs. I and 2, carrler 6 Includes a paTr of parallel endless conveyor assemblles 10 and 12 which are spaced apart along the length of fuselage 18 a distance corresponding to the len~th of an ALM. These conveyor assem-blies extend about the periphery of fuselage 18 In transverse a~ignment wlth the longttudlnal axis thereof. Assemblles 10 and 12 are Identical and therefore only assembly 10 is descrlbed In detall hereinafter, llke parts of assembly 12 belng desig-nated wlth the same reference numerals, prlmed.
Referrlng now to conveyor assembly 10 as Illustra~ed In Figs. 2-6, conveyor assembly 10 is made up of a sectlonal gulde track ~generally referenced 19) which supports and guidas an endless posltlonlng chaln 34 of length sufflclent to enclrcle fuselage 18. Chaln 34 Is moved wlth respect to track 19 by a posltionlng motor 44, to be descrlbed presently. Track 19 is composed of a plurality of elongated guide track sectlons 20 whlch are secured end-to-end by connectlng links Z4, Z6 and . ~ , :' t 1'~ 9 contractable couplings 2&~ 30. Couplings 28, 30 ar~ contrac--table 50 as to exert a tensile force on sections 20 to apply a compressive radial force about the periphery of the fuselage 18 for maintainTng -track 19 in an operative conformal positlon 9 as illustrated in Flg. 2. (The track sections wTII be described in more detail hereinafter.) Referring to Fig~ 39 chain 34 Is made up of muitiple elongated load bearing elements 58 which are connected together at their ends by articulated 17nks 60. The guide track sectlons gulde the chaTn along a curved channel in whTch the chaTn Is confTned laferally but is freely movable in a circumferential dir~ction. To this end, track section 20 Tncludes upstanding : sTdewalls 62, 64 which terminate in Tips 66, 68. Thesa lips overlap the edges of the chain 34 and serve to retain Tt within the channel. The chaTn, of course, is unrestrained as Tt travels between the ends of adjacent track sections as illustrated in Flg. 2; however, Tt possesses sufficient laterlal rlgldity that It does not tend to become misaligned during these intervals of travel.
An important aspect of thls inventlon Is that the guide tracl< sectlons are conformable to a range of fuselage contours.
That Is, the guide track sections are sufficiently flexlble that they will conform to the contour of the underlying portTon of the aircraft fuselage. As a consequence, the gulde track sectlons may be applted to the aircraft fuselage at different locatTons which exhlblt varying curvatures and may be applTed to dlfferent aircrafi-. Furthermore, the guide track sections are sufficient-ly flexlble to enable the fuselage shape to change In fllght : 30 stresses without creatlng excesslve local stress concentratlons.
To thls end, the track sectlon Includes side openings 70 of C-shaped outllne whlch are formed in the sidewalls 62, 64 and terminate In slots 72 whlch extend transversely of lips 66, 68.
Slots 72 are of sufficlent width that, wlth the track sectton posttloned wTth openlngs 70 facing outwardly from the fuselage, the track sectlon can flex radially to assume a range of curva-tures. The track section obtained Is thus rigld wifh respect to longitudlnal and laterial forces, but is flexible with respect to radlal forces~ Referring to Fi~. 6, a typical track sectlon is illustrated in three load condttions freestandlng ~ref-erenced A) wherein it presents Its smallest radius of curvature, under essentially no-load conditlons~ nominal (referenced B) whereln tt is forced to conform to i-he nominal fuselage radlus of curvature, shown here as sl1ghtly larger than in A; and max-Imum radius of curvaturs (referenced C) wherein ii~ is subjected to the maximum flexural load in the plane of the conveyor assembly 10~ W1th thts construction, the track section will assume a radlus of curvature whlch conforms to the radius of curvature of the underlying portlon of the fus21age when the track sectlon is subJect~d to an appropriate tensile force applied along its length. The guide track section Is composed of an appropriate material, such as alumlnumJ having desired flexural and load bearlng properties.
Thus, it is possibleJ by applying sufflcient tenslle force to the Interconnected track sectlons uslng couplings 2~
and 30, to grlp the sxterior of ihe fuselage 18 so as to generaie sufflcient frictlon forces to prevent relativa motion of gu7de track 19 wtth respect to the fuselage~ both In the axial and the peripheral directlons. If, however, thls condltion Is not satlsfied; that ts, If the contact forces are Insufflclen-i to ensure the absence of such relative motlon under condltions of allowable clrcumferential forces~ seml-permaneni adhestve mat-erlal 73 could be applied between the Inslde ~rack surface andthe fuselage skin. The effect of thls adheslve Is to Increase, by a substantial factor, the contact or gripplng forces be-tween the guide track and the fuselage skln. For an equlvalent magnltude of contact forces, thls would aliow the reductlon of the hoop ~clrcumfsrential) tension and thereby the radlal com-presslve force applled to the fuselage. The adheslve shoulcl be preferably seml-permanent so that followlng th~ completion of mllltary mlsstons, the gulde track could be removable by application of relatlvely small separatlon forces~ Thereafter, the adheslve can be sanded or cleaned off so as to restore the origlnal condltion of the fuselage.
It may be required to relnforce the fuselage Inter-nally agalnst the addltlonal static loads imposed by the aforementioned radial compresslve forces and dynamtc loads , ' ~1~2~79 g resulttng from the gravlty and inertlal forces acting upon the payload packages and other components formtng part of the con-veyor assembly. R~ferr1ng to Ftg. 10, expandable radial braces : 5 50 may be connected between longitudinal braclng beams 52 and the aircraft floor structure 54, so as to offer addl-tional support : agalnst radial loads without causing excesslve forcss to act on the floor structure. addltional circumferential supports 56 also could be mounted by beams 52, as shown. In most prac-ilcal ALM carrler applications, such relnforcement should not bs re-qulred. If used, however, the relnforcement should be config-: ured In such a manner as to permlt assembly~ tensionlng, dls-assembly, and dTsposal of the payload carrisr without modifi-cation of the primary aircraft structure.
Referring now to Figs. 7-9, tracks i9 and 19' and respectively assoclated positionlng chalns 34 and 34~ are mounted onto the exterlor of fuselage 18 for supportlng the ends of an ALM. Supports 36 and 361 are assembled to chaTns 34 and 34'~ respoctively, for supportlng the ends of the ALM.
As an ALM carrler of multiple ALM's as depicted in Flgs. 8 and 9, multtple ALM~s (ALM I - 10) are carrled in parallel align~
ment wlth the longttudinal a~is of fuselage 18. Indivldual drlve motors 44, 46 are connected to and drlve these chalns In unison. In the example, these motors are elec-trTcally pow-ered and are connected by respecttve power transmisslons 70, 72to chains 19 and 191. In operation, these motors move the chalns In unlson a predetermTned ciistance and maintain the chalns at a selected Index position. The motors may move the chalns bl-dlrectlonally, or conttnuously, to present a S9 lected ALM or other payload item at an ejectlon station which, In the example, Is located adjacent the underslde or belly of fuselage 18. ~ALM 10 Is located a-t the eJectlon statlon In Fl~. 9.) The ALM is eJeoted by releastng It from supports 36, 36~ and allow-lng It to drop away from the alrcraft. An approprlate ejecilon devlce could be used to apply a force to the ALM for tnltlally separatTng It from the aircraft. Thus, the ALM~s may be eJected In a predetermlned sequence, or a selected ALM may be ejected out-of-sequence, as the case may be. By controlltng release oF
the ALM occupylng the eJection station9 of course, it would be posslble to move an ALM past the eJectlon statton, whtch there-after may be occup1ed by a succaedtng ALM or other payload item.
The former ALM, of course, could be returned to the ejectton statlon at a later tlme by reverse movement.
A fatring 48 may be mounted by the tracks 19 and 19 and provldes an aerodynamlcally shaped shell type surface sur-roundTng the ALM s~ as depicted In Figs. 7 - 9. As tllustrated In Ftg. 9~ Falr7ng 48 tncludes ejectlon doors 49 at the ejec tlon statlon. These doors are opened to eJact an ALM.
To convert a commerctal aircraft to an ALM carrier, the gulde track sections are secured snugly around the outer surface of the alrcraft $uselage at approprlate locatlons and are subjected to sufflclent tensloning effort that frlctional ~rlpptng forcos will be applied to the alrcra~t skln. Once the tracks are in posltlon, the posTtioning chains ars assembled in place. The posttionlng motor or motors are now mounted to the fuselage, together wlth approprtate hydraullc or electrlcal circults and drlvlng mechantsm ts~ so that, upon recelvlng the appropriaie command slgnalJ the position!ng chains wlll meve in elther directlon or stop Tn a specified Index positlon.
The drlve assembly Is so designcd that two or more positionlng chains whlch belong to the same group of two or more conformable gulde tracks retatn their relatlve peripheral posltlons when drlven by the positlonlng motors. The assembly comprtsing two or several movable posittoning chains 1n the corresponding number of guide tracks is now ready to receive the payload pack-ages, whlch for the purposes of this descriptton are assoclated with roughly cylindrically-shaped misslles. The missile packagss are now mounted io the posltlonlng chalns In posltton around the perlphery of the fuselage. Followlng these assembly op~ratlons, the reversible converslon Is complete and the alr-craft Is ready to undertake Its milttary mlssion ~s).
In typlcal mllltary mlssion, the alrcraft is flown to the launch area uslng Its own navigation and communlcatlon equlpment. The initlaltzatlon messages to the mlssiles, I.e., the electronically conveyed slgnals to be stored In the mtsslles which glve navigatlon and weapon arming and fuslng Information, are generated by the proper milltary command and control systam :~7~79 . , I--electronics communicatlon equipment. The tnitlalIzatlon is stored either directly In the mlsslles or auxillary interface equlpment on board the alrcrafi-. The latter may be lodged In remo~able pallets, loaded and conneoted to the payload prior to take-off. The launch commands are then generated by the mill--ary comm~nd and control system and are aither relayed diractly to the missiles via the onboard co~lunications equlpment, or prestorad Tn the aircraft and released via an enabling launch message sent to the aircraft personnel which in turn wlll generate the actual launch commands. The missile to be launched Is so positioned that it faces the eJection door, the missiler is launched and the operation ls rep~ated untll such time as the entlre carrler Is empty or the mission orders are mod1fied. Following the missile launch, the air-craft returns to its original base or to an alternate base and Is elther reloaded or refurblshed. If for some reason the mlsslles are not lawnched~ they ara returned to the home base or Jettlsoned in fllght.
Referrlng agatn to Fig. 7, falring 48 reduces drag at the expense of addltlonal welght and cost. For long-range mtsstons, such as transatlantic ranges for example, the cirag reduction offered by the fairings Is often found mandatory.
For much shorter ranges or when aerial refueling Is posslble, the need for reduclng drag is much less imperatlve. It Is thus posslble, for those mlsslons less sensitive to drag, to ellmlnate fairTng entlrely, or shape the guide tracks in a manner whlch offers some measure of aerodynamical~y desirable proflle in the longitudinal dlrectTon.
Referrlng to Fig. 17, an expendable fairlng 48 also could be used in place of a track mounted falrlng 48. In thls instance9 after assembly of the payload packages to the poslt10n-lng chalns, the Intersttces between the AiM s and the fuselags as well as the spaces between the ALM~s could be ftlled wlth llghtweight, fast-curing material, such as urethane foam, for example, The external surface of this material could be molded In the deslrable aerodynamlc shape and coated externally wlth smooth palnt or s1mllar materlal and formed to rupture upon eJection of any one of the ALM s. This rupture would occur In ~ 2 ~
the entirety of th~ molded fairlng whan the ALM is ejected, or along mechanlcally weakened fault ITnes which cause fracture of the moldlng portion associated with any one or several mlssiles.
Electrlcal wlres 83 could be embedded In the molded falrlng as depicted in i~lg. 17 to produce fracture along predetermined In-ternal surfaces foilowlng the passage of current In these wlres when fracture is desTred. In the Illustrated example, a portlon o~ falrlng 48 has been fractured and removed durlng eJectlon of ALM 10 ~not shown), with fracture having occurred along para-llel fault llnss formed by wTres a3. In the expendable fairlng, of course It is essential that: pr70r to, and following par~ial launch of missiles, the relatlve moi-lon of the ALM s in the perTpheral directlon under the actton o$ the positlonlng motors i5 must not perceptibly interact with the alrcraft or mlsslle motlons and structures; and followlng partlal or compiete launch .- of the mlssiles, the then remalning portlon of the molded falr-Ing does not signlficantly degrade the theretofore experlenced drag performance.
Z0 A modlfled drlve assembly Is Illustrated In figs~ 14 and 15. In thls assembly, a motor Is essentlally inst~lled in the place of one payload package and is mounted on posltionin~
chain 34. A sultable reduction gear tratn 86 transmlts power from motor 84 to a fixed rack 88 which forms part of a con-25 formable guide track 90 ~see FTg. 15). A motor 92, gear train 84, and rack 96 are associated with parallel gulde track 98.
These motors are operated in unison to e~ert forces on racks 88 and 96 to drlve the posltionlng chains wlth respect to thalr respective gulde tracks.
Referrlng to Figs. Il and 12, when the payload packages are relatlvely short, more than two gulde tracks may ; be employed under the same faTring. The deslgn cholce Is to use elther two chaln tracks with the payload packages such as ALM s mounted on an auxll7ary stiffentng structure 100 as deplcted in Flgs. Il and 12, or to use more than two tracks, wlth the Intermedlary track serving both mlssiles assembled along the same generatrlx of the fuselage as deplci-ed In Flg. 3.
The concept can be expanded to cover comblnations of the above in order to sarve more than two missiles mounted along the same ,:
, .
:, ;.
generatrix. Whatever the number of gulde tracks serving a given carrier, of course, the positioning motors must be mechanlcally or elactrically synchronized so that in ths course of perlpheral motton of tha positionlng chalns, the relatlve posltion of all missiles w711 be preserved.
Referrlng to Fig. 16, a slngle forward carrler ~referenced 80) may be reloaded wlth fresh AU~Is carrled externally to the fuselage 18. To thls end, external tubes, tracks or channels are installed along any one or several of the fuselage generatrix llnes. These channels or loading tracks may be used to store, and upon proper commanci to cilsplace In the axlal directlon~ ml~slles or other payload packages simllar In nature and shape to those described hereinabove.
An axemplary assemblage of loading tracks, dlsplacement meclt-antsms, payload packages and aerodynamlc falring surfaces as a dorsal loadlng structure 82 installed on the upper lat-eral surface of the fusetage is Illustrated in Fig. 16. In the example, structure 82 includes three parallel tubes 84, 8~, 88 whlch termlnate at thelr front ends in coaxlal allgn-mant with three adJacent Index posltlons of carrler 80. A
dorsal falrtng 90 is mounted on the fuselage.
Once the mlsslles or other payload packages have been launched from the carrler 80, the mlssilas or payload packages s~ored in the dorsal loading structure 82 are moved forwardly In the ax7al dlrectton vta tubes 84, 86~ 88 to effec~ reload.
The posltioning chalns are for thls purposa stopped In the pos-ltion required to accept one, two, or threa fresh mlssl 19s from tube~ 84, 86, 88. Followlng acceptance of three fresh mlsslles9 the chains are rotated to advanca three index pos-ltlons for additlonal raloadlng. Thls loadlng operatlon is repeated untll all ALM posltlons are occupled by fresh misslles or untll the reload misslle supply is exhausted.
; For use wlth alrcraft equlpped wtth a forward cargo door, a slngle carrler could be mounted by ths aft portion of ths fuselage as Illustrated by carrler 8 in Flg. 1. Tv reload this carrier, missTles or payload packages are trans-ferred to the carriar 8 from Inside the aircraft via the cargo door and then rearwardly along the external loadlng 1 1~2~
1~-track generally similar to structure 82. In thls case, carrler 8 need not Include a f~Tring and the loadlng track requlres a mlnlmal fairlng. Carrler 8 remains empty untll the alr~raft approaches a dellvery location, at whlch tlm~ the carrler Is loaded~
To maintaln in-flight balance ~hen only a slngle foward carrler Is usedJ elther reserve fuel or movable ballast should be loaded In the aft portion o~ the fuselaye and reposl-IO tloned automa~icaliy as the mlsslles are expendsd. Scme Inertballast wlll be requlred to ensure proper balance in the case ~ where the fuel reservs is exhausted and the alrplans must return - to base without having launched its mtssiles. Slmtlar balanclng techntques9 of course, may be used when only a slngle aft carrler Is used.
Although one preferrad embodl,ment of the inventlon has been Illustrated and described herelnJ varlatlons wlll become apparent to one of ordinary sklll tn the art. Accordlngly~ the Invention Is not to be 17mited to the spectfic embodiment Illu-strated and described hereln, and the tr~e scope of the InventTon ; ts to be determined by reference to the appended c1alms.
.,' r -.
. . .
.
.. .
. , .
:
' ;
~ : -
such as misslles or cannlsters are attached to the outside of the aircraft, In this instance, of course, drag and aero-elastic stability problems become important conslderatlons. In general, structural modlficattons are requlred to provide the hard point or mounting posts upon which the load can be attached. Drag can be avoTded by provldlng approprlate fairlngs~ but with current destgns tusually referred to as conformal carrlages), such falrtngs must also be attached to the structural strong potnts o~ the aircraft. Once again, structural modlflcatlons to the extent that thoy cause payload panalty and avallabillty loss are - undeslrable as expiained above. Another form of external carry makes use of a rotary rack, such as that used In military alr-craft, mounted in an aerodynamically shaped pod to be carrlsd on a single strong-potnt bullt tn one of the wings of certain commerclal aTrcraft. (The original design purpose of the strong-point was to carry a spare englne). The military payload that can be carried under such condltlons, however9 Is of limited welght.
~O SUMMARY OF THE INVENTION
The present invention provldes a payload carrler for detachable mounting on selected vehtcles havlng bodles whlch are of c~oss-sectlonal outlines within a predetermlned range of , outllnas~ the carrier comprlsfng: guide means engagable wlth the :25 exterior of a vehlcle body about the perlphery thereof; and pay-load posltlonlng means operatively assoclated wlth sald gulde means for movement wiih respect thereto to move a payload article ;~wlth respect to the body perlphery toward a payload eJectlon statlon a~ which the payload article may be released; sald guide means Includtng means conformable to the cross-sectional outllne of the body for applylng a compressive force about the body perlphery to malntaln said guide means In a flxed posltlon thereon.
The present inventlon also provides a method for converiing an alrcraft to an ALM carrler alrcraft, comprlslng the steps of: securlng gulde track means to the alrcraft fuselage about the perlphery thereof essenttally by applytng a peripheral compressive force thereto; and mounting payload posittonlng means to satd gulde meàns for suppor~tng a plura-~' I il r7 2 ~ ~j) 9 --4--lity of ALMIs In parallel alignment with the longitudinal axis of -he fusalage for movement with respect to the fuselage peri-- phery toward an ajectlon station at which an ALM may be releasad, whereby the aircraft may be converted to an ALM carrler and may be refurbished to Its prlor conditlon with essentlally no mod-ificatlon to the fuselage or the structure.
More specifically, the present Inventton provldes a carrier adapted for an external carry configuratlon wherain one or more ALM~s rnay be carrted by an aircraft whlch i5 re-verslbly converted for milTtary usage. As a consequence, any atrcraft of appropriata payload capacity may, using thls inven-tTon, be reversibly converted Into a mllitary payload or ALM
carrier yleldlng acceptable flight parformance, with mlnimal structural modificatton. Followlng military operatlons, the alrcraft may be refurbished for non-milTtary use. Thls Inven-tlon therefore offers to make a natlon s commercial alrllne ~leet, military transport aircraft, and other avallable alrcraft as milltary payload carrters, especlally as ALM carrlers. The Inventlon also offers the posslbillty of convertlng mlll-iary alrcraft, design for other uses, to ALM carrlers, in a reversi-ble modec According to one preferred embodlment of ihe inven-tion, the carrler Includes one or rr,ore conformable guide tracks whlch are secured under tenslon to the a;rcraft fuselage at spaced apart locations along the length thereof. An endless flexlble posltionlng chain Is mounted Inside of each track and Is freely movable about the perlphery of the fuselage Irres-pective of the exact shape of the fuselage In cross-sectlon or of deformatlons therein under flight loads. The positloning chains are motor drlven and so posittonable that payload packages attached thereto can be moved In sequen-iai or arbitrarily chosen ordsr from any inltial posltion along the fuselage perlphery Into the ejection (launch) posltion (s). For ALM applicatton, multlple mlsslles are carrled about the fuselage perlphery In parallel alignment with the longttudlnal axis of the fuselage and are supported at their ends by iwo spaced apart gulde tracks and associated positioning chains. A permanent or jettlson-able fairing surrounds the carrier to ensure relatlvely modest 1 ~72~79 addltlonal drag caus0d by the addltional payload. Excesstve structural loads can be absorbed, if necessary, by Internal braclng of the fuselage. Accordlng to further aspects of the S invention for AUM application in particular, additional ALM s may be carrTed in externally afflxed channels or tracks for reloading. If the slze of the missiles permlt, Internally carried missiles could be loaded into the externai channeis by a transfer device Installed In tha cargo door.
These and other features, obJects, and advantages of ~he present Invention wlll becvme apparent from the detalied description and clalms to follow, taken In conJunction with the accompanying drawings in which lilce parts bear llke reference numerals.
BR_EF DESCRIPTION OF THE DRAWINGS
FIG. I is a perspective of an alrcraft equipped wTth two carrlers according to thls invention, the carriers mounted `- fore and aft of -the wing~
' FIG. 2 is a fragmentary perspectlve of the forward : 20 Flg. I carrler;
FIG. 3 is a perspective of one gulde track section and associated positlonTng chaln of the Flg. 2 carrier;
FIG. 4 Is a perspective of the Flg. 3 gulde track;
FIG. 5 Is a slde elevation of the Fig. 4 guide track;
FIG. 6 is a slde elevation generally stmliar to Fig. S
but ~n expanded scale of one end of the guide track In dlfferent posltlons;
FIG. 7 is a perspectlve of the Fig. I forward carrler wlth a falring and supportlng an ALM payload;
FIG, 8 Is a section talcen along the llna 8-8 in Flg. 7;
FIG. 9 is a sectlon taken along the llne 9-9 In Flg. 8;
FIG. 10 Is a section taken along the llne 10-10 tn Flg. 2;
FIG. Il Is a side elevatlon of a modifled payload suppor~;
FIG. 12 Is an end elevatlon of the Flg. Il support;
FIG. 13 is a side elevatlon of a second mQdlfied payload support;
FIG. 14 Is a perspective generally slmilar to Fig. 7 l 1~2~1'7~
of a modlfied chaln drive assembly9 FIG. 15 Ts a fragmentary perspectlve on enlarged scale of the guide track of the Flg. 14 assembly;
FIG. 16 is a perspectlve generally slmllar to Fig. 1 of an aircraft equlpped wi-th a single carrler ~falring not shown for clari ~) and a reloading assembly;
FIG. 17 is a fragmentary sectlon generally slmllar to Flg, 9 of the forward carrier wilh an expendable falrtng) IO depictlng the fairlng wIth a portlon removed to permit taunch of an ALM.
DE~AILED DESCRIPTiON OF THE DRAW ! NGS
Referrlng to Ftg. I of the drawings, a jet transport aircraft may be eguipped wlth one or more carrters of this ~ 15 invention to reverslbly convert ~hat aircraft Tnto an ALM
;~ carrler. In the example Illustrated In Fig. 1, two carriers 6 and ~ ara detachably mounted on the aircraft fuselage 18 fore and aft of wing 21, respectlvely. Fig~ 16 depici-s a simllar aircraft equipped wtth a slngle forward carrler and a dorsally located reloading assembly, to be descrlbed presently. The Flg. I carrlers 6 and 8 are essentlally Identlcal and therefore only carrler 6 Is described In detall herelnafter.
~ aferrfng now to Flgs. I and 2, carrler 6 Includes a paTr of parallel endless conveyor assemblles 10 and 12 which are spaced apart along the length of fuselage 18 a distance corresponding to the len~th of an ALM. These conveyor assem-blies extend about the periphery of fuselage 18 In transverse a~ignment wlth the longttudlnal axis thereof. Assemblles 10 and 12 are Identical and therefore only assembly 10 is descrlbed In detall hereinafter, llke parts of assembly 12 belng desig-nated wlth the same reference numerals, prlmed.
Referrlng now to conveyor assembly 10 as Illustra~ed In Figs. 2-6, conveyor assembly 10 is made up of a sectlonal gulde track ~generally referenced 19) which supports and guidas an endless posltlonlng chaln 34 of length sufflclent to enclrcle fuselage 18. Chaln 34 Is moved wlth respect to track 19 by a posltionlng motor 44, to be descrlbed presently. Track 19 is composed of a plurality of elongated guide track sectlons 20 whlch are secured end-to-end by connectlng links Z4, Z6 and . ~ , :' t 1'~ 9 contractable couplings 2&~ 30. Couplings 28, 30 ar~ contrac--table 50 as to exert a tensile force on sections 20 to apply a compressive radial force about the periphery of the fuselage 18 for maintainTng -track 19 in an operative conformal positlon 9 as illustrated in Flg. 2. (The track sections wTII be described in more detail hereinafter.) Referring to Fig~ 39 chain 34 Is made up of muitiple elongated load bearing elements 58 which are connected together at their ends by articulated 17nks 60. The guide track sectlons gulde the chaTn along a curved channel in whTch the chaTn Is confTned laferally but is freely movable in a circumferential dir~ction. To this end, track section 20 Tncludes upstanding : sTdewalls 62, 64 which terminate in Tips 66, 68. Thesa lips overlap the edges of the chain 34 and serve to retain Tt within the channel. The chaTn, of course, is unrestrained as Tt travels between the ends of adjacent track sections as illustrated in Flg. 2; however, Tt possesses sufficient laterlal rlgldity that It does not tend to become misaligned during these intervals of travel.
An important aspect of thls inventlon Is that the guide tracl< sectlons are conformable to a range of fuselage contours.
That Is, the guide track sections are sufficiently flexlble that they will conform to the contour of the underlying portTon of the aircraft fuselage. As a consequence, the gulde track sectlons may be applted to the aircraft fuselage at different locatTons which exhlblt varying curvatures and may be applTed to dlfferent aircrafi-. Furthermore, the guide track sections are sufficient-ly flexlble to enable the fuselage shape to change In fllght : 30 stresses without creatlng excesslve local stress concentratlons.
To thls end, the track sectlon Includes side openings 70 of C-shaped outllne whlch are formed in the sidewalls 62, 64 and terminate In slots 72 whlch extend transversely of lips 66, 68.
Slots 72 are of sufficlent width that, wlth the track sectton posttloned wTth openlngs 70 facing outwardly from the fuselage, the track sectlon can flex radially to assume a range of curva-tures. The track section obtained Is thus rigld wifh respect to longitudlnal and laterial forces, but is flexible with respect to radlal forces~ Referring to Fi~. 6, a typical track sectlon is illustrated in three load condttions freestandlng ~ref-erenced A) wherein it presents Its smallest radius of curvature, under essentially no-load conditlons~ nominal (referenced B) whereln tt is forced to conform to i-he nominal fuselage radlus of curvature, shown here as sl1ghtly larger than in A; and max-Imum radius of curvaturs (referenced C) wherein ii~ is subjected to the maximum flexural load in the plane of the conveyor assembly 10~ W1th thts construction, the track section will assume a radlus of curvature whlch conforms to the radius of curvature of the underlying portlon of the fus21age when the track sectlon is subJect~d to an appropriate tensile force applied along its length. The guide track section Is composed of an appropriate material, such as alumlnumJ having desired flexural and load bearlng properties.
Thus, it is possibleJ by applying sufflcient tenslle force to the Interconnected track sectlons uslng couplings 2~
and 30, to grlp the sxterior of ihe fuselage 18 so as to generaie sufflcient frictlon forces to prevent relativa motion of gu7de track 19 wtth respect to the fuselage~ both In the axial and the peripheral directlons. If, however, thls condltion Is not satlsfied; that ts, If the contact forces are Insufflclen-i to ensure the absence of such relative motlon under condltions of allowable clrcumferential forces~ seml-permaneni adhestve mat-erlal 73 could be applied between the Inslde ~rack surface andthe fuselage skin. The effect of thls adheslve Is to Increase, by a substantial factor, the contact or gripplng forces be-tween the guide track and the fuselage skln. For an equlvalent magnltude of contact forces, thls would aliow the reductlon of the hoop ~clrcumfsrential) tension and thereby the radlal com-presslve force applled to the fuselage. The adheslve shoulcl be preferably seml-permanent so that followlng th~ completion of mllltary mlsstons, the gulde track could be removable by application of relatlvely small separatlon forces~ Thereafter, the adheslve can be sanded or cleaned off so as to restore the origlnal condltion of the fuselage.
It may be required to relnforce the fuselage Inter-nally agalnst the addltlonal static loads imposed by the aforementioned radial compresslve forces and dynamtc loads , ' ~1~2~79 g resulttng from the gravlty and inertlal forces acting upon the payload packages and other components formtng part of the con-veyor assembly. R~ferr1ng to Ftg. 10, expandable radial braces : 5 50 may be connected between longitudinal braclng beams 52 and the aircraft floor structure 54, so as to offer addl-tional support : agalnst radial loads without causing excesslve forcss to act on the floor structure. addltional circumferential supports 56 also could be mounted by beams 52, as shown. In most prac-ilcal ALM carrler applications, such relnforcement should not bs re-qulred. If used, however, the relnforcement should be config-: ured In such a manner as to permlt assembly~ tensionlng, dls-assembly, and dTsposal of the payload carrisr without modifi-cation of the primary aircraft structure.
Referring now to Figs. 7-9, tracks i9 and 19' and respectively assoclated positionlng chalns 34 and 34~ are mounted onto the exterlor of fuselage 18 for supportlng the ends of an ALM. Supports 36 and 361 are assembled to chaTns 34 and 34'~ respoctively, for supportlng the ends of the ALM.
As an ALM carrler of multiple ALM's as depicted in Flgs. 8 and 9, multtple ALM~s (ALM I - 10) are carrled in parallel align~
ment wlth the longttudinal a~is of fuselage 18. Indivldual drlve motors 44, 46 are connected to and drlve these chalns In unison. In the example, these motors are elec-trTcally pow-ered and are connected by respecttve power transmisslons 70, 72to chains 19 and 191. In operation, these motors move the chalns In unlson a predetermTned ciistance and maintain the chalns at a selected Index position. The motors may move the chalns bl-dlrectlonally, or conttnuously, to present a S9 lected ALM or other payload item at an ejectlon station which, In the example, Is located adjacent the underslde or belly of fuselage 18. ~ALM 10 Is located a-t the eJectlon statlon In Fl~. 9.) The ALM is eJeoted by releastng It from supports 36, 36~ and allow-lng It to drop away from the alrcraft. An approprlate ejecilon devlce could be used to apply a force to the ALM for tnltlally separatTng It from the aircraft. Thus, the ALM~s may be eJected In a predetermlned sequence, or a selected ALM may be ejected out-of-sequence, as the case may be. By controlltng release oF
the ALM occupylng the eJection station9 of course, it would be posslble to move an ALM past the eJectlon statton, whtch there-after may be occup1ed by a succaedtng ALM or other payload item.
The former ALM, of course, could be returned to the ejectton statlon at a later tlme by reverse movement.
A fatring 48 may be mounted by the tracks 19 and 19 and provldes an aerodynamlcally shaped shell type surface sur-roundTng the ALM s~ as depicted In Figs. 7 - 9. As tllustrated In Ftg. 9~ Falr7ng 48 tncludes ejectlon doors 49 at the ejec tlon statlon. These doors are opened to eJact an ALM.
To convert a commerctal aircraft to an ALM carrier, the gulde track sections are secured snugly around the outer surface of the alrcraft $uselage at approprlate locatlons and are subjected to sufflclent tensloning effort that frlctional ~rlpptng forcos will be applied to the alrcra~t skln. Once the tracks are in posltlon, the posTtioning chains ars assembled in place. The posttionlng motor or motors are now mounted to the fuselage, together wlth approprtate hydraullc or electrlcal circults and drlvlng mechantsm ts~ so that, upon recelvlng the appropriaie command slgnalJ the position!ng chains wlll meve in elther directlon or stop Tn a specified Index positlon.
The drlve assembly Is so designcd that two or more positionlng chains whlch belong to the same group of two or more conformable gulde tracks retatn their relatlve peripheral posltlons when drlven by the positlonlng motors. The assembly comprtsing two or several movable posittoning chains 1n the corresponding number of guide tracks is now ready to receive the payload pack-ages, whlch for the purposes of this descriptton are assoclated with roughly cylindrically-shaped misslles. The missile packagss are now mounted io the posltlonlng chalns In posltton around the perlphery of the fuselage. Followlng these assembly op~ratlons, the reversible converslon Is complete and the alr-craft Is ready to undertake Its milttary mlssion ~s).
In typlcal mllltary mlssion, the alrcraft is flown to the launch area uslng Its own navigation and communlcatlon equlpment. The initlaltzatlon messages to the mlssiles, I.e., the electronically conveyed slgnals to be stored In the mtsslles which glve navigatlon and weapon arming and fuslng Information, are generated by the proper milltary command and control systam :~7~79 . , I--electronics communicatlon equipment. The tnitlalIzatlon is stored either directly In the mlsslles or auxillary interface equlpment on board the alrcrafi-. The latter may be lodged In remo~able pallets, loaded and conneoted to the payload prior to take-off. The launch commands are then generated by the mill--ary comm~nd and control system and are aither relayed diractly to the missiles via the onboard co~lunications equlpment, or prestorad Tn the aircraft and released via an enabling launch message sent to the aircraft personnel which in turn wlll generate the actual launch commands. The missile to be launched Is so positioned that it faces the eJection door, the missiler is launched and the operation ls rep~ated untll such time as the entlre carrler Is empty or the mission orders are mod1fied. Following the missile launch, the air-craft returns to its original base or to an alternate base and Is elther reloaded or refurblshed. If for some reason the mlsslles are not lawnched~ they ara returned to the home base or Jettlsoned in fllght.
Referrlng agatn to Fig. 7, falring 48 reduces drag at the expense of addltlonal welght and cost. For long-range mtsstons, such as transatlantic ranges for example, the cirag reduction offered by the fairings Is often found mandatory.
For much shorter ranges or when aerial refueling Is posslble, the need for reduclng drag is much less imperatlve. It Is thus posslble, for those mlsslons less sensitive to drag, to ellmlnate fairTng entlrely, or shape the guide tracks in a manner whlch offers some measure of aerodynamical~y desirable proflle in the longitudinal dlrectTon.
Referrlng to Fig. 17, an expendable fairlng 48 also could be used in place of a track mounted falrlng 48. In thls instance9 after assembly of the payload packages to the poslt10n-lng chalns, the Intersttces between the AiM s and the fuselags as well as the spaces between the ALM~s could be ftlled wlth llghtweight, fast-curing material, such as urethane foam, for example, The external surface of this material could be molded In the deslrable aerodynamlc shape and coated externally wlth smooth palnt or s1mllar materlal and formed to rupture upon eJection of any one of the ALM s. This rupture would occur In ~ 2 ~
the entirety of th~ molded fairlng whan the ALM is ejected, or along mechanlcally weakened fault ITnes which cause fracture of the moldlng portion associated with any one or several mlssiles.
Electrlcal wlres 83 could be embedded In the molded falrlng as depicted in i~lg. 17 to produce fracture along predetermined In-ternal surfaces foilowlng the passage of current In these wlres when fracture is desTred. In the Illustrated example, a portlon o~ falrlng 48 has been fractured and removed durlng eJectlon of ALM 10 ~not shown), with fracture having occurred along para-llel fault llnss formed by wTres a3. In the expendable fairlng, of course It is essential that: pr70r to, and following par~ial launch of missiles, the relatlve moi-lon of the ALM s in the perTpheral directlon under the actton o$ the positlonlng motors i5 must not perceptibly interact with the alrcraft or mlsslle motlons and structures; and followlng partlal or compiete launch .- of the mlssiles, the then remalning portlon of the molded falr-Ing does not signlficantly degrade the theretofore experlenced drag performance.
Z0 A modlfled drlve assembly Is Illustrated In figs~ 14 and 15. In thls assembly, a motor Is essentlally inst~lled in the place of one payload package and is mounted on posltionin~
chain 34. A sultable reduction gear tratn 86 transmlts power from motor 84 to a fixed rack 88 which forms part of a con-25 formable guide track 90 ~see FTg. 15). A motor 92, gear train 84, and rack 96 are associated with parallel gulde track 98.
These motors are operated in unison to e~ert forces on racks 88 and 96 to drlve the posltionlng chains wlth respect to thalr respective gulde tracks.
Referrlng to Figs. Il and 12, when the payload packages are relatlvely short, more than two gulde tracks may ; be employed under the same faTring. The deslgn cholce Is to use elther two chaln tracks with the payload packages such as ALM s mounted on an auxll7ary stiffentng structure 100 as deplcted in Flgs. Il and 12, or to use more than two tracks, wlth the Intermedlary track serving both mlssiles assembled along the same generatrlx of the fuselage as deplci-ed In Flg. 3.
The concept can be expanded to cover comblnations of the above in order to sarve more than two missiles mounted along the same ,:
, .
:, ;.
generatrix. Whatever the number of gulde tracks serving a given carrier, of course, the positioning motors must be mechanlcally or elactrically synchronized so that in ths course of perlpheral motton of tha positionlng chalns, the relatlve posltion of all missiles w711 be preserved.
Referrlng to Fig. 16, a slngle forward carrler ~referenced 80) may be reloaded wlth fresh AU~Is carrled externally to the fuselage 18. To thls end, external tubes, tracks or channels are installed along any one or several of the fuselage generatrix llnes. These channels or loading tracks may be used to store, and upon proper commanci to cilsplace In the axlal directlon~ ml~slles or other payload packages simllar In nature and shape to those described hereinabove.
An axemplary assemblage of loading tracks, dlsplacement meclt-antsms, payload packages and aerodynamlc falring surfaces as a dorsal loadlng structure 82 installed on the upper lat-eral surface of the fusetage is Illustrated in Fig. 16. In the example, structure 82 includes three parallel tubes 84, 8~, 88 whlch termlnate at thelr front ends in coaxlal allgn-mant with three adJacent Index posltlons of carrler 80. A
dorsal falrtng 90 is mounted on the fuselage.
Once the mlsslles or other payload packages have been launched from the carrler 80, the mlssilas or payload packages s~ored in the dorsal loading structure 82 are moved forwardly In the ax7al dlrectton vta tubes 84, 86~ 88 to effec~ reload.
The posltioning chalns are for thls purposa stopped In the pos-ltion required to accept one, two, or threa fresh mlssl 19s from tube~ 84, 86, 88. Followlng acceptance of three fresh mlsslles9 the chains are rotated to advanca three index pos-ltlons for additlonal raloadlng. Thls loadlng operatlon is repeated untll all ALM posltlons are occupled by fresh misslles or untll the reload misslle supply is exhausted.
; For use wlth alrcraft equlpped wtth a forward cargo door, a slngle carrler could be mounted by ths aft portion of ths fuselage as Illustrated by carrler 8 in Flg. 1. Tv reload this carrier, missTles or payload packages are trans-ferred to the carriar 8 from Inside the aircraft via the cargo door and then rearwardly along the external loadlng 1 1~2~
1~-track generally similar to structure 82. In thls case, carrler 8 need not Include a f~Tring and the loadlng track requlres a mlnlmal fairlng. Carrler 8 remains empty untll the alr~raft approaches a dellvery location, at whlch tlm~ the carrler Is loaded~
To maintaln in-flight balance ~hen only a slngle foward carrler Is usedJ elther reserve fuel or movable ballast should be loaded In the aft portion o~ the fuselaye and reposl-IO tloned automa~icaliy as the mlsslles are expendsd. Scme Inertballast wlll be requlred to ensure proper balance in the case ~ where the fuel reservs is exhausted and the alrplans must return - to base without having launched its mtssiles. Slmtlar balanclng techntques9 of course, may be used when only a slngle aft carrler Is used.
Although one preferrad embodl,ment of the inventlon has been Illustrated and described herelnJ varlatlons wlll become apparent to one of ordinary sklll tn the art. Accordlngly~ the Invention Is not to be 17mited to the spectfic embodiment Illu-strated and described hereln, and the tr~e scope of the InventTon ; ts to be determined by reference to the appended c1alms.
.,' r -.
. . .
.
.. .
. , .
:
' ;
~ : -
Claims (18)
1. A payload carrier for detachable mounting on selected vehicles having bodies which are of cross-sectional outlines within a predetermined range of outlines, the carrier comprising: guide means engagable with the exterior of a vehicle body about the periphery thereof; and payload position-ing means operatively associated with said guide means for movement with respect thereto to move a payload article with respect to the body periphery toward a payload ejection station at which the payload article may be released; said guide means including means conformable to the cross-sectional outline of the body for applying a compressive force about the body peri-phery to maintain said guide means in a fixed position thereon.
2. The carrier of Claim 1, wherein said guide means include a conveyor assembly made up of guide track means adapted to encircle the body and wherein said payload position-ing means include an endless chain which is guided by said guide track means for movement with respect to the body periphery.
3. The carrier of Claim 29 wherein said guide track means include a plurality of elongated guide track sections and means for securing said sections together in end-to end relation under a tensile load sufficient to apply said compressive force.
4. The carrier of Claim 3, wherein each said track section includes a continuous inner surface adapted to contact the body exterior, and lateral confinement means upstand-ing from said surface for containing said chain to move along a peripheral path, said confinement means including a plurality of openings spaced along the length of said track section to enable said track section to be curved so as to maintain said surface in conforming contact with the body exterior when said track section is subjected to said tensile load.
5. The carrier of Claim 2, wherein said conveyor assembly includes means mounted by the vehicle and acting be-tween the vehicle and said chain for moving said chain with respect to said guide track means.
6. The carrier of Claim 2, wherein said conveyor assembly includes means mounted by said chain and acting between said chain and said guide track means for moving said chain with respect to said guide track means.
7. A removable external payload carrier for reversibly converting an aircraft to an ALM carrier aircraft, the carrier comprising: guide means engagable with the air-craft fuselage about the periphery thereof; and payload posi-tioning means for supporting a plurality of ALM's in parallel alignment with the longitudinal axis of the fuselage and opera-tively associated with said guide means for movement with res-pect thereto to move an ALM with respect to the fuselage peri-phery toward an ejection station at which an ALM may be released;
said guide means including means conformable to the cross-sectional outline of the fuselage for applying a compressive force about the fuselage periphery to maintain said guide means in a fixed position thereon.
said guide means including means conformable to the cross-sectional outline of the fuselage for applying a compressive force about the fuselage periphery to maintain said guide means in a fixed position thereon.
8. The carrier of Claim 7, including fairing means operatively associated with said guide means and said payload positioning means for surrounding the ALM's.
9. The carrier of Claim 8, wherein said fairing means include an aerodynamic shell mounted by said guide means, said shell including an opening adjacent said ejection station, and door means for closing said opening until an ALM
is to be released.
is to be released.
10. The carrier of Claim 8, wherein said fairing means include material forming an aerodynamic surface, and means for removing a portion of said surface adjacent said ejection station when an ALM is to be released.
11. The carrier of Claim 7, including means mounted by the fuselage exterior for reloading said payload positioning means by positioning a fresh ALM for support there-by in a location for movement toward said ejection station.
12. The carrier of Claim 7 wherein said guide means include two conveyor assemblies each made up of guide track means adapted to encircle the fuselage and wherein said payload positioning means include an endless chain which is guided by said guide track means for movement with respect to the fuselage periphery, and means mounted by said chain for supporting the end of an ALM.
13. The carrier of Claim 12, wherein said guide track means include a plurality of elongated guide track sections and means for securing said sections together in end-to-end relation under a tensile load sufficient to apply said com-pressive force.
14. The carrier of Claim 13, wherein each said track section includes a continuous inner surface adapted to contact the fuselage exterior, and lateral confinement means upstanding from said surface for confining said chain to move along a peripheral path, said confinement means including a plurality of openings spaced along the length of said track section to enable said track section to be curved so as to main-tain said surface in conforming contact with the fuselage ex-terior when said track saction is subjected to said tensile load.
15. The carrier of Claim 12, wherein said conveyor assembly includes means mounted on the fuselage and acting be-tween the fuselage and said chain for moving said chain with respect to said guide track means.
16. The carrier of Claim 12, wherein said conveyor or assembly includes means mounted by said chain in piece of an ALM and acting between said chain and said guide track means for moving said chain with respect to said guide track means.
17. A method for converting an aircraft to an ALM
carrier aircraft, comprising the steps of: securing guide track means to the aircraft fuselage about the periphery thereof essentially by applying a peripheral compressive force thereto;
and mounting payload positioning means to said guide means for supporting a plurality of ALM's in parallel alignment with the longitudinal axis of the fuselage for movement with respect to the fuselage periphery toward an ejection station at which an ALM may be released, whereby the aircraft may be converted to an ALM carrier and may be refurbished to its prior condition with essentially no modification to the fuselage or the struc-ture.
carrier aircraft, comprising the steps of: securing guide track means to the aircraft fuselage about the periphery thereof essentially by applying a peripheral compressive force thereto;
and mounting payload positioning means to said guide means for supporting a plurality of ALM's in parallel alignment with the longitudinal axis of the fuselage for movement with respect to the fuselage periphery toward an ejection station at which an ALM may be released, whereby the aircraft may be converted to an ALM carrier and may be refurbished to its prior condition with essentially no modification to the fuselage or the struc-ture.
18. The method of Claim 17, including applying a layer of adhesive to the aircraft fuselage for securing said guide track means thereto.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CA000389597A CA1172479A (en) | 1981-11-06 | 1981-11-06 | Removable external payload carrier for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CA000389597A CA1172479A (en) | 1981-11-06 | 1981-11-06 | Removable external payload carrier for aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1172479A true CA1172479A (en) | 1984-08-14 |
Family
ID=4121349
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA000389597A Expired CA1172479A (en) | 1981-11-06 | 1981-11-06 | Removable external payload carrier for aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CA (1) | CA1172479A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2015112853A1 (en) * | 2014-01-24 | 2015-07-30 | L-3 Communications Integrated Systems L.P. | Reconfigurable payload systems (rps) for aircraft |
-
1981
- 1981-11-06 CA CA000389597A patent/CA1172479A/en not_active Expired
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2015112853A1 (en) * | 2014-01-24 | 2015-07-30 | L-3 Communications Integrated Systems L.P. | Reconfigurable payload systems (rps) for aircraft |
| US9669927B2 (en) | 2014-01-24 | 2017-06-06 | L-3 Communications Integrated Systems L.P. | Reconfigurable payload systems (RPS) with operational load envelopes for aircraft and methods related thereto |
| US9676482B2 (en) | 2014-01-24 | 2017-06-13 | L-3 Communications Integrated Systems L.P. | Reconfigurable payload systems (RPS) for aircraft and methods related thereto |
| US10202193B2 (en) | 2014-01-24 | 2019-02-12 | L-3 Communications Integrated Systems L.P. | Reconfigurable payload systems (RPS) with operational load envelopes for aircraft and methods related thereto |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US4318328A (en) | Removable external payload carrier for aircraft | |
| US5927653A (en) | Two-stage reusable earth-to-orbit aerospace vehicle and transport system | |
| US9493227B2 (en) | Method and system for loading and unloading cargo assembly onto and from an aircraft | |
| US12065267B2 (en) | Earth to orbit transportation system | |
| US4256012A (en) | Missile launcher for aircraft | |
| US6394392B1 (en) | Aircraft having multiple fuselages | |
| US4471926A (en) | Transfer vehicle for use in conjunction with a reusable space shuttle | |
| US4943014A (en) | Soft ride method for changing the altitude or position of a spacecraft in orbit | |
| US5411226A (en) | Spacecraft adapter and dispenser | |
| RU2175933C2 (en) | Means method and system for launching spacecraft on basis of towed glider | |
| US8814097B2 (en) | Mounting set, system and method | |
| EP1013546A2 (en) | Rocket payload fairing and method for opening same | |
| US7861972B1 (en) | Release mechanism for a forward and aft restrained load in an aircraft | |
| US4575029A (en) | Spacecraft for use in conjunction with a reusable space shuttle | |
| US3929306A (en) | Space vehicle system | |
| US5763811A (en) | Internal weapon carriage system for wide body aircraft | |
| CA1172479A (en) | Removable external payload carrier for aircraft | |
| US5441221A (en) | Heavy-lift vehicle-launched space station method and apparatus | |
| RU2121939C1 (en) | Cargo compartment for lighter-than-air flying vehicle (versions) | |
| EP0078858A1 (en) | Removable external payload carrier, in particular for aircraft | |
| US5402968A (en) | Collapsible fuel tank system | |
| CN112124625A (en) | Ship and rocket integrated shuttle aircraft and flight control method | |
| US20050120638A1 (en) | Bulkhead assembly | |
| US20240246701A1 (en) | VTOL aircraft-conducted soft capture, preserving and landing of spacecrafts | |
| RU2093431C1 (en) | Recoverable space vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| MKEC | Expiry (correction) | ||
| MKEX | Expiry |