Abstract:
A missile separation system for fixedly attaching a rocket motor section   a payload section has cofunctioning attaching and retarding means integrated to retain plural sections of a missile system in mated relationship until a predetermined point in the missile flight path.

Description:
BACKGROUND OF THE INVENTION 
     1. Field of the Invention 
     This invention relates to separation assemblies and more particularly to a missile section separation assembly. 
     2. Description of the Prior Art 
     Missiles are conventionally made from a plurality of sections which are designed so as to be separable during the missile flight at a predetermined point in the flight path. For example the booster or motor section of the missile is usually separated from the remaining portion of the missile during the flight after the propellant in the booster section has been expended. 
     The separation assembly of this invention has utility in numerous separable combinations although it is primarily intended for use in target or research missiles. This type of missile is presently being utilized for high altitude targets or the collect high altitude atmospheric data. They are commonly made from two parts which include a rocket motor section and a payload section. Near the apex of the missile&#39;s trajectory, the payload section and the rocket motor section are separated and a parachute is deployed. The parachute functions to support the missile as it falls slowly through the target area or while it collects atmospheric data and relays that information electronically to the ground. 
     SUMMARY OF THE INVENTION 
     The missile separation system of this invention includes a rocket motor section interconnected to a payload section which houses electronic equipment and the like, by a separation or canister section. The canister section is detachably attached to the payload section utilizing peripheral recesses associated therewith in conjunction with explosive bolts in communication with these recesses for rigidly mating the canister section with the payload section. The canister section is also provided with an air brake system or retarding means for insuring the separation of the missile elements. 
     With the foregoing in mind it is a principal objective of this invention to provide a relatively uncomplicated and inexpensive separation system for positively and efficiently separating plural sections of a component system such as a missile system. 
     More particularly, an object of this invention is a missile canister section for joining together a rocket motor section and a payload section which canister section insures a clean separation of the missile components along a predetermined separation interface. 
     Yet another object of the invention is the incorporation of a retarding structure within a missile separation assembly to enhance the separation of the canister section from the payload section. 
     These and other objects of the invention will become more readily apparent from the following specification when read in light of the drawings. 
    
    
     BRIEF DESCRIPTION OF THE DRAWINGS 
     The present invention is illustrated in the accompanying drawings of which: 
     FIG. 1 is a sectional view of a missile embodying the invention; 
     FIG. 2 is an exploded view of the missile separation system; and 
     FIG. 3 is a perspective view taken along line 3--3 of FIG. 2. 
    
    
     DESCRIPTION OF THE PREFERRED EMBODIMENT 
     Referring to the drawings wherein like reference characters designate corresponding parts throughout the several figures, a missile indicated generally by the reference character 10, of conventional configuration is formed of three principle sections. A rocket motor section 12 interconnected to a separation or canister section 14 and a payload section 16 which houses electronic equipment such as measuring and transmitting equipment, programming devices and the like. Canister section 14 and rocket motor section 12 are joined together by conventional means forming no part of the present invention. 
     With reference to FIGS. 2 and 3, canister section 14 defines a central cavity 18 open on one end for receiving and housing a deployable parachute 20 which is provided with cord 22 for attachment to a U-bolt 24 in payload section 16. When canister section 14 and payload section 16 are joined together as more clearly described below, the base 26 of the payload section forms a cover over cavity 18 for retention of the parachute until sectional separation. 
     As shown in FIGS. 1 and 3, a pair of longitudinally aligned primary peripheral recesses 28 defining front, side and rear walls 30, 32, 34, and bottom 36 are located on opposing sides of canister section 14. On opposing sides of these primary recesses 28 are located secondary recesses 38 in parallel alignment along the longitudinal axis and in communication with the primary recesses. Proximate the rear walls 34 of each primary recess 28 as best shown in FIG. 3 is a threaded bore 40 and an opposing smooth bore 42 aligned with the threaded bore. This smooth bore 42 communicates with the exterior surface 44 of the canister section 14. The front wall 30 of each primary recess 28 is provided with a connecting bore 46. When the canister section 14 and payload section 16 are joined, these bores 46 form a passageway between each primary recess 28 in the canister section and peripheral channels 48 within each payload section. 
     As depicted in FIGS. 2 and 3, within each canister section primary recess 28 are axially aligned braking or retarding means indicated generally by numeral 50. These retarding means define rectangular shaped retarding structures 50 having arcuate shaped surfaces 52, front, side and rear walls 54, 56, 58, and bottoms 60. Each structure 50 includes a bulkhead wall 62 vertically disposed between front and rear walls 54 and 58 defining front and rear chamber 64 and 66. Each front wall 54 and bottom 60 have circular openings 68 and 70 communicating with the front 64 and rear 66 chambers respectively. A spring 72 or other resilient means is retained within each rearmost chamber 66 and extends through opening 70 with one end of each spring in contact with the bottom 36 of each recess 28. 
     On the side walls 56 near the rear wall 58 of each retarding structure 50 are located opposing transverse aligned smooth bores 74 extending through the side walls 56 and in alignment with threaded bore 40 and smooth bore 42 located on opposing side walls 32 of each primary recess 28 when each retarding structure is fixedly mounted in each primary recess. 
     For a detailed description of the assembly of the payload 16 and canister sectons 14 according to the present invention, reference is made to FIGS. 1, 2, and 3. Rocket motor section 12 and canister section 14 are assembled in conventional fashion. Payload section 16 is next fixedly attached to the canister section 14 by joining the payload and canister section such that primary peripheral recess connecting bores 46 are aligned with each payload peripheral channel 48. With the canister section connecting bores 46 and payload section peripheral channels 48 aligned an explosive bolt 80 of conventional design is inserted into the passage formed by the aligned bores and recesses such that the bolt head 82 is located in the payload section recess and the threaded end 84 of the bolt is within the canister section recess. Attachment of a bolt nut 86 to the threaded end 84 of each bolt 80 fixedly attaches the canister 14 and payload 16 section together. The retarding structures 50 are then slideably pushed forward and down, into the primary recesses 28 until circular openings 68 within front walls 54 contact and close over each bolt nut 86 in locking engagement. Simultaneously, each spring 72 or other suitable resilient member is compressed within each canister recess 28. Upon placement of a retarding structure 50 within the recesses 28, a retaining pin 76 having a threaded end 78 is inserted through bore 42 and smooth bores 74 until the threaded end of the retaining pin is received within the threaded bore 40. By this arrangement the retarding structures 50 are pivotally retained at their aft ends and are temporarily interlocked at their fore ends within each recess 28 associated therewith. In this fashion the retarding structures 50 provide a smoothly fitting cover over each canister recess 28. 
     Each payload recess is further provided with a cover plate (not shown) and explosive bolt functioning or actuating means 88 including electric leads 90 communicating with signaling and triggering means for applying a potential to detonate the explosive bolts 80 and separate the payload 16 and canister 14 sections. 
     After missile 10, assembled according to the disclosed invention has been launched and attains a predetermined altitude it becomes necessary to separate and recover the payload section 16 from the other missile components. Programmed instrumentation contained with the payload section 16 actuates or causes an electrical discharge to function the explosive bolts 80. Simultaneous detonation of the bolts 80 sever the bolts allowing separation of the payload section 16 from the canister section 14. The force of the exploding bolts 80 forces the bolt nuts 86 rearwardly to impact upon bulkhead 62 within each retarding structure 50. The force of the bolt nuts 86 impacting on the bulkhead wall 62 imparts an upward and rearward movement to the retarding structures 50. This allows the arcuate surface 52 to interact with the slipstream passing over the missile surface. As this occurs the retarding structures 50 are deployed to about a 45 degree angle effecting a braking action thereby enhancing separation of the payload section 16 from the canister section 14. The coiled resilient spring 72 uncoils at the same time the retarding structure 50 is deploying as backup to insure that the retarding structures deploy. The system design is such however that the retarding means will function without spring assistance. As the canister section 14 is separating from the payload section 16, the parachute 20 retained within the canister cavity 18 deploys to provide controlled descent of the payload section for subsequent recovery. 
     The preferred embodiment disclosed above positions the explosive bolts such that the bolt heads are located in the payload section, the bolt nut ends are in the primary recesses of the canister section and the actuating means are retained within the payload section. 
     It is understood however that another embodiment would reverse the bolts such that the bolt heads are located in the canister section primary recesses, the bolt nut ends are in the payload section and the actuating means housed in the canister section. Actuation of the explosive bolts in this configuration would cause the bolt heads to strike the bulkheads of each retarding structure effecting deployment of the retarding means. 
     The foregoing descriptions in conjunction with the appended claims constitute a disclosure such as to enable the invention to be made and used by those skilled in the missile arts. Further, the structures herein described meet the objectives of the invention and constitute an advance in the art unobvious to persons not having the benefit of the teachings contained herein. 
     Obviously, many modifications and variations of the present invention are possible in light of the above teachings and it is therefore to be understood that within the scope of the disclosed inventive concept, the invention may be practiced other than as specifically described.