Patent Publication Number: US-3880383-A

Title: Control flap unit for projectiles or rockets

Description:
United States Patent l l Voss et al.  
 l l CONTROL FLAP UNIT FOR PROJECTILES ()R ROCKETS [751 Inventors: Alfred Voss. Cologne:  
 Heinz-Wilhelm Kreutz. Troisdorf-Oherlar; Heinz Kroschel, Troisdorf-Sieglar: Manfred Strunk. Neuenvade all of Germany [73] Assignee: Dynamit Nobel Aktiengesellschaft Troisdorf. German {22] Filed: June 4. i973 [Zll Appl. No.: 366,519  
 Primary E.nln1irm&#39;\erlin R Pendegrass Attorney. Agent. or Firm-Craig 8; Antonelli |57| ABSTRACT A control flap unit for a projectile of the type having on Apr. 29. 1975 a rudder carrier extending longitudinally and a pluralit of guiding fins attached to the rudder carrier for pivotal movement about respective pivot axes extend ing perpendicular to the longitudinal axis of the pro jectile. A sliding sleeve is disposed internall of the rudder carrier for engagement with pivot levers mounted eccentrically with respect to the fin pivot HYES so as to move the fins from a folded condition ex tending longitudinall along the outside of the rudder carrier to an in-flight position extending radiallv with respect to the rudder carrier. Lateral guide slots are provided in the rudder carrier for guiding the mounting end portions of the fins. Also, Curved pi\ot le\er guide slots are prmided in the rudder carrier all for guiding the pivot levers to effect the pivotal movement of the fins in response to longitudinal movement of the pivot le\ers resulting from engagement with the mo\ ahlt: sliding sleeve. These pivot lever guide slots are constructed with an extension forwardly of the lateral slots so as to accommodate attachment and detachmerit of the fins with fixedly attached pivot levers onto the rudder carrier by merely inserting the pi\ot levers through the most forward portions of the pi\ot leier guide slot and then moving the fin into position in the lateral slots where the fins are pivotall connected to the rudder carrier h to oifurther connecting mean through aligned apertures in the fins and the rudder carrier.  
 14 Claims. 4 Drawing Figures CONTROL FLAP UNIT FOR IROJECTILES OR ROCKETS BACKGROUND AND SUMMARY OF THE INVENTION This invention relates to a control flap unit for projectiles or rockets of the type having control fins guided in lateral slots in the tail of a rudder carrier of the projectile or rocket. which fins can be unfolded about axes arranged at transverse and preferably right angles to the longitudinal axis of the projectile or rocket. tangentially to the rudder or control unit carrier. It has been contemplated to utilize a sliding sleeve which can he moved rearwardly within the rudder carrier to press against pivot levers eccentrically mounted to the fins and extending through the rudder carrier from the outside in circular-aro-shaped slots.  
  In DAS (German Published Application) l.l98.248. a control flap unit is described for projectiles or rockets which can be fired from the barrel ofa gun. wherein the rudder carrier has a longitudinal bore wherein a sliding sleeve is disposed which can be moved axially by means of a spring force. This sliding sleeve presses. with its rear end. against pivot levers arranged at the rudders or tins and thus unfolds. after the projectile or rocket has left the gun barrel. the fins about axes extending at right angles to the longitudinal axis of the projectile or rocket. tangentially to the rudder carrier. into the flying position. The pivot levers extend from the outside through the rudder carrier in circular-arc-shaped slots. In order to avoid as far as possible any fluttering movements of the fins during flight. which reduce the target accuracy. the fins are additionally guided in the zone of their mounting end in lateral slots in the rear or tail por tion of the rudder carrier. The tail of the rudder carrier is provided with a correspondingly larger outer diameter as compared to the remaining portion of the rudder carrier to accommodate these lateral slots.  
  If. as is generally customary for projectiles or rockets of the type contemplated by the present invention. the tail or rear portion is made integral with the remaining portion of the rudder carrier. then it is necessary. in order to mount the fins. to insert the latter without the pivot levers in the lateral slots with their mounting end. and thereafter to attach the pivot levers. The reason therefor is that the circular-arc-shaped slots for the pivot levers are effectively entirely covered by rudder carrier tail portion structure which accommodates the lateral slots. The subsequent mounting of the pivot levers. however. is extremely cumbersome. since corresponding bolts must be inserted from the inside of the rudder carrier through the circular-arc slots to the mounting end of the fins and then must be threadedly joined to the latter. for example. In order to avoid an improper release of the pivot levers during the transport of the projectiles or rockets. it is customary to secure this threaded connection additionally by gluing or cementing. Consequently. a disassembly of a rudder. which perhaps has been partially damaged. is no longer possible. Additionally. there is the danger that glue residues impede the flawless unfolding of the fins and thereby make the functioning of the projectile or rocket questionable.  
  This invention is based on the problem of avoiding the above-mentioned disadvantages. i.e.. to simplify. on the one hand. the assembly of the tail unit and. on the other hand. to increase the operational safety thereof.  
  This problem is solved. in accordance with this invention. for a control flap unit of the type mentioned in the foregoing. by providing that the circular-arc-shaped slots are prolonged or extended toward the front past the zone of the lateral slots. preferably oriented in the direction of the longitudinal axis of the projectile. This extension makes it advantageously possible to mount the fins together with the pivot lever already attached to the fins. by first inserting the pivot lever from the outside in the uncovered portion (portion longitudinally spaced from the lateral slots) of the extension of the circular-arcshaped slot. and then placing the fin with its mounting end into the respective lateral slot. the pivot lever more or less sliding into the circular-arc slot during this step. Thereafter. the fin may he attached with known connecting means. for example by a screw connection. in the rear of the rudder carrier.  
  The ahove-described arrangement of the present invention considerably reduces the complications previously encountered as discussed above in the assembly of the rudder or tail unit on a projectile with foldahle fins. The operational safety of the projectile is also improved by the above-described arrangement of the present invention. since the pivot levers can be fixedly connected to the fins hy fashioning the pivot levers. for example. as integral bolts or pins which. prior to the assembly of the fins on the rudder carrier. are reliably joined thereto in the manner of a rivet connection. so that even very large lateral forces can be flawlessly absorbed.  
  Attention is also directed to our copending US. patent application titled PROJECTILE OR ROCKET PREFERABLY WITH UNFOLDABLE TAIL UNIT. filed June 4. I973 and based on German application P 22 27 l04.l. for further disclosure of the type of projectile contemplated by the present invention. To the extent necessary for a complete understanding of the present invention. the disclosure of said copending application is incorporated herein by reference.  
 BRIEF DESCRIPTION OF THE DRAWINGS These and further objects. features and advantages of the present invention will become more obvious from the following description. when taken in connection with the accompanying drawings which show. for purposes of illustration only. a single embodiment in accordance with the present invention. and wherein FIG. I is a longitudinal partially sectional view illustrating a projectile or rocket with a control flap unit constructed in accordance with the present invention:  
  FIG. 2 is an enlarged longitudinal view of the rear of the rudder carrier which shows a part of the control flap unit of FIG. I with the fins removed;  
  FIGS. 30 and 311 show a fin in two different views. likewise on an enlarged scale.  
 DETAILED DESCRIPTION OF THE DRAWINGS i.e..  
  Referring to FIG. I. the projectile or rocket with a nose 1 and a one-piece intergral rudder carrier 2 is provided. at the tail 3 shown in a longitudinal sectional view. with fins 4 shown in the unfolded condition. e.e.. in the flying position. In the interior of the rudder carrier 2. a sliding sleeve 5 is shown with a compression spring 6 disposed in front thereof. The annular collar 7 of the sliding sleeve 5 contacts pivot levers 8 guided in slots 9 of the rudder carrier 2. The fins 4, in turn. are guided in the lateral slots 10.  
  In FIG. 2. the tail 3 of the projectile or rocket is shown prior to the assembly of the fins. The tail 3 is provided. on the one hand. with the lateral slots l and. on the other hand. with the circular-arc-shaped slots 9 of which only one is shown for reasons of illustra tion. Each ofthe circulanarc-shaped slots 9 have an extension ll extending forwardly of front end 12 of the lateral slots [2 toward the nose I. These extensions 1] are preferably provided in the direction of the longitudinal axis of the projectile or rocket so as to simplify the manufacture thereof. However. these extensions 11 can basically also be ofany desired curved shape within the intendment ofthe present invention. However. it is important that the extensions I] extend past the front end 12 of the lateral slots toward the front. in order to make it possible to introduce the pivot levers S fixedly mounted to the [ins 4. The tail 3 is furthermore provided with bores l3 of which likewise only one is illlustrated wherein the fins 4 are attached with a conventional means to be pivotable tangentially with respect to the rudder carrier 2 about respective pivot axes extending perpendicular to the longitudinal axis or centerline of the projectile.  
  The fin 4 shown in a lateral view in FIG. 3a is fixedly joined to the pivot lever at its mounting end 14 by riveting as shown in a sectional view the upper portion ofthe pivot lever into the head [5. In FIG. 3b. the same fin 4 is shown in a plan or top view. with the illustration of mounting bore 16 which is associated with the bore 13 in the rudder carrier 2 for accommodating a screw or the like through bores l3 and I6 to pivotally mount the tin to the rudder carrier.  
  While we have shown and described only one embodiment in accordance with the present invention. it is understood that the same is not limited thereto but also contemplates numerous changes and modifications as would be known to those skilled in the art given the present disclosure of the invention. and we therefore do not wish to be limited to the details shown and described herein only schematically but intend to cover all such changes and modifications.  
 We claim:  
 I. A control flap unit for a projectile comprising:  
 a one piece integral rudder carrier extending in the direction ofa longitudinal axis of the projectile and having a rear portion of larger cross-sectional di mensions than a more forward portion immediately adjacent thereto.  
 at least one guiding fin means attached to said rudder carrier for pivotal movement about respective pivot axes extending transverse to said longitudinal axis pivot lever means mounted on each of said fin means eccentrically with respect to respective ones of said fin pivot axes.  
 lateral fin guide slot means in said rear portion for accommodating pivotal movement of radially inward portions of said fin means,  
 pivot lever guide slot means in said carrier engageable with said pivot lever means for effecting pivotal movement of said fin means about said respective pivot axes in response to longitudinal movement of said pivot lever means. said pivot lever guide slot means extending from said rear portion forwardly into said more forward portion to ac commodate attachment and detachment of said fin means viith said pivot lever means fixedly mounted thereto; and  
 longitudinally movable abutment means in said carrier engageable with said pivot lever means to im part longitudinal movement to said pivot lever means.  
  2. A control flap unit according to claim 1, wherein said pivot lever guide slot means are of circulanarcshaped configuration over the portion thereof in said rear portion of the rudder carrier and are of longitudinally extending straight configuration over the portion thereof in said more forward portion of the rudder car rier.  
  3. A control flap unit according to claim 2, wherein said pivot axes extend perpendicular to said longitudinal axis.  
  4. A control flap unit according to claim 3, wherein said fin means are movable between a storage position extending tangential to said rudder carrier along said more forward portion and an in-use flight position extending radially with respect to said rear portion.  
  5. A control flap unit according to claim 3. wherein said longitudinally movable abutment means is a sliding sleeve disposed inside said rudder carrier. and wherein said sliding sleeve abuts radially inward end portions of said pivot lever means.  
  6. A control flap unit according to claim 5. wherein radially outward end portions of said pivot lever means engage said pivot lever guide slot means in said rear portion.  
  7. A control flap unit according to claim I. wherein each lateral fin guide slot means in said rear portion is defined by opposing faces. each respective pivot lever guide slot means in said rear portion being formed in both faces of respective lateral fin guide slot means. each respective pivot lever means engaging respective pivot lever guide slot means on both faces of each respective lateral fin guide slot means.  
  8. A control flap unit according to claim 1, wherein said rudder carrier defines a channel along its longitudinal axis. each pivot lever guide slot means radially communicating between said channel and the outer surface of said rudder carrier.  
  9. A control flap according to claim I, wherein a plurality of fin means are provided.  
  10. A control flap unit according to claim 9, wherein six fins are provided.  
  11. A control flap unit according to claim 10. wherein said upper portion is essentially hexagonal in cross-section.  
  12. A control flap unit according to claim 9. wherein said upper portion is essentially polygonal in crosssection. each side of the polygon corresponding with one of said fin means.  
  13. A control flap unit according to claim I, wherein said pivot lever guide slot means forwardly extends in said forward portion by a distance sufficient so that said fin means can clear the forwardmost part of said rear portion of said rudder carrier when the pivot lever means engages the forwardmost part of said pivot lever guide slot means.  
  14. A process for assembling a control flap unit useful for a projectile and including:  
 a one-piece integral rudder carrier extending in the direction ofa longitudinal axis of the projectile and having a rear portion of larger cross-sectional dimensions than a more forward portion immediately adjacent thereto,  
 at least one guiding fin means attached to said rudder carrier for pivotal movement about respective pivot axes extending transverse to said longitudinal axis,  
 pivot lever means mounted on each of said fin means eccentrically with respect to respective ones of said fin pivot axes,  
 lateral fin guide slot means in said rear portion for accommodating pivotal movement of radially inward portions of said fin means,  
 pivot lever guide slot means in said carrier engageable with said pivot lever means for effecting pivotal movement of said fin means about said respective pivot axes in response to longitudinal movement of said pivot lever means, said pivot lever guide slot means extending from said rear portion forwardly into said more forward portion to accommodate attachment and detachment of said fin means with said pivot lever means fixedly mounted thereto, and  
 longitudinally movable abutment means in said carrier engageable with said pivot lever means to impart longitudinal movement to said pivot lever means;  
 said process comprising:  
 positioning said longitudinally movable abutment means in said carrier such that the portion of said longitudinally movable abutment means engageable with said pivot lever is aligned essentially with the forwardmost portion of said pivot lever guide slot means; positioning said fin means in association with said rudder carrier with said pivot lever means passing through the forwardmost portion of said pivot lever guide slot means and engaging said longitudinally movable abutment means, said fin means further being aligned with said lateral fin guide slot means; moving said abutment means and said fin means until said rudder carrier and tin means are aligned with respect to their common pivot axis; and rotatably securing said fin means and said rudder carrier together at their common pivotal axis.