US3903803A

US3903803A - Missile separation means

Info

Publication number: US3903803A
Application number: US028809A
Authority: US
Inventors: William A Losey
Original assignee: US Department of Navy
Current assignee: US Department of Navy
Priority date: 1960-05-12
Filing date: 1960-05-12
Publication date: 1975-09-09
Anticipated expiration: 1992-09-09

Abstract

1. In a missile of the type having a ballistic missile component and a booster motor adapted to propel the missile component during the boost phase of its trajectory, the booster motor having a forward section and the missile component being disposed so as to co-extensively abut the forward section, the improvement comprising; an annular member secured to the forward edge of said section and extending inwardly thereof, said member having an outwardly facing recess, a plurality of studs disposed inwardly of said missile component and affixed thereto, said studs having indented portions projecting into and being at least in part contiguous with said recess, a locking band, and releasable means holding a locking portion of said band tightly within said recess and against said indented portions for securely connecting said missile component to said section.

Description

United States Patent 1191 Losey Sept. 9, I975 MISSILE SEPARATION MEANS V Primary ExuminerVerlin R. Pendegrass [75] Inventor. W|ll1am A. Losey, Sunnyvale. Calif. -v g or Firm R. S sciascia; C. [73] Assignee: The United States of America as Funkhouser; D, Evrard represented by the Secretary of the Navy, Washington, DC. EXEMPLARY CLAIM Filedi y 1960 1. In a missile of the type having a ballistic missile [2| Appl 28,809 component and a booster motor adapted to propel the missile component during the boost phase of its II'8JC tory, the booster motor having a forward section and /4 B the missile component being disposed so as to co- [5] Illtl F42b 15/12 extensively abut the forward section, the improvement [58] Field of earch Z/ /1 B; comprising; an annular member secured to the for- 285/7 ward edge of said section and extending inwardly thereof, said member having an outwardly facing re [56] R r nc Cited eess, a plurality of studs disposed inwardly of said mis- UNITED STATES PATENTS sile component and affixed thereto, said studs having 2,489,984 11/1949 Shoemaker 119/1112 indented Portions P f and belng 2,649,736 8/1953 Phillips 89/102 P11rt comlguous Wllh 831d recess. lockmg i and 2,757,942 8/1956 Eberhart 285/7 releasable means holding a locking portion of said 2,809,584 lO/l957 Smith 102/49 band tightly within said recess and against said in 2l 8/1959 Arditow 1, 285/7 dented portions for securely connecting said missile 2,932,352 4/1960 Korn 102/49 component to Said Section 2,959,l29 |l/l96() Warren. lU2/49 2,996,316 8/1961 Terhune 102 49 4 Claims. 9 Drawing Figures PATENTEI] SEP 9 I875 sum 2 o g INVENTOR William A. Losey ATTORNEYS PATENTEU SEP 1 75 saw 3 or 4 BY W (9M ATTORNEYS INVENTOR William A. Lasey BY M yaw/44W ATTORNEYS SHEET 0F 4 PATENTED SEP 9 i975 FIG. 6

I Sepamhon LPlane l 24 MISSILE SEPARATION MEANS This invention relates to ballistic missiles and more particularly to means for effecting separation of the missile from the booster motor.

Means have been proposed to effect separation between a booster rocket motor and a forwardly attached component comprising an annulus of Primacord or similar type explosive placed in juxtaposition with the surface of an interconnecting skirt or the like, detonation of the explosive serving to sever the skirt circumferentially for effecting separation of the component from the booster motor. However, it has been found that the amount of explosive required to effect separation by this means is considerable and that the interconnecting skirt is not always cut evenly, the effect of which is to cause undesirable perturbations to be imparted to the component so as to cause it to depart from the desired ballistic trajectory.

In another form of separation means which has been employed heretofore, an externally disposed segmental ring of channel cross section is provided with confronting inner surfaces which are adapted to engage sloping surfaces formed on outwardly extending flanges on a rocket motor and a forwardly attached component, respectively, for holding the motor and component together. The segments of the ring are interconnected by explosive bolts which are adapted to be detonated when release of the segmental ring and separation of the component from the motor is desired; see US. Pat. No. 2,809,5 84, issued Oct. I5, 1957, to Bernard Smith. Such separation apparatus has projecting parts which do not make for a smooth outer skin of the motor and its component thereby adding to the drag of the missile in flight.

The present invention provides releasable locking means for detachably securing together a booster rocket motor and a forwardly attached component and explosively actuated means for releasing the locking means. The locking means is disposed inwardly of the outer skin of the motor-component system and is adapted to unlock upon release thereof to effect a positive and smooth separation of the component from the motor.

It is therefore an object of the present invention to provide an improved and reliable connection between a booster motor and another missile component.

Another object is to provide an improved detachable connection between a booster motor and a forwardly attached ballistic component which permits separation of the component from the motor without applying to the component, during separation, deflecting forces which would cause the component to depart from the desired ballistic trajectory intended therefor.

A further object of the invention is to provide a segmental locking band for detachably connecting a ballistic missile to a booster motor, the segments of the band being adapted to be forced apart for affecting smooth separation of the missile from the motor.

Still another object is to provide locking means comprising segments of spring metal and connecting means between the segments, the connecting means being adapted to be ruptured by explosive means for releasing the segments and permitting them to spring outwardly for affecting smooth separation of the missile component from the motor.

Yet another object of the invention resides in the provision of a volume of pressurized gas between the missile component and the booster motor whereby upon release of means connecting the component to the motor. expansion of the gas uniformly forces the component away from the motor for a smooth separation thereof without the existence of an unbalanced condition of the forces acting on the booster and componcnt.

Other objects and many of the attendant advantages of the present invention will be readily appreciated as the same becomes better understood by reference to the following detailed description when considered in connection with the accompanying drawings wherein:

FIG. I is an exploded perspective view of a ballistic missile system with which the separation means of the present invention is associated;

FIG. 2 is a diagrammatic view illustrating the function of the separation means of this invention during the flight of the missile system;

FIG. 3 is a fragmentary side view of the missile system showing the joint between the missile component and the booster motor;

FIG. 4 is a cross-sectional plan view taken substantially along the line 4-4 of FIG. 3, as viewed in the general plane of the separation means of the present invention;

FIG. 5 is a detailed view on a larger scale showing the cross section of the annulus located at the forward end of the equipment section of the missile system;

FIG. 6 is a detailed view of a larger scale taken sub stantially along the line 66 of FIG, 4 and illustrates the manner in which the segmental locking band secures the missile component to the equipment section;

FIG. 7 is a detailed view on a larger scale taken sub stantially along the line 77 of FIG. 4 and depicts the manner in which the fairing strip is secured to the locking band.

FIG. 8 is a fragmentary detailed view, partly in sec tion, showing the T-bolt connector between the ends of the pair of segments of the locking band and the explosive means employed for rupturing the connector to release the locking band; and

FIG. 9 is a view of another form of explosive means which may be employed for releasing the segments of the locking band.

Referring now to the drawings, wherein like reference characters designate like or corresponding parts throughout the several views, there is disclosed in FIG. 1 a ballistic missile system with which the separation means of the present invention may be associated. The components of the missile system are shown separated for a better understanding thereof. The missile system comprises a first stage solid propellant rocket booster motor 11 having propulsion control means 12, a second stage solid propellant rocket booster motor 13 with its propulsion control means l4, and an interconnecting skirt section 15 which joins the rocket motors and is adapted to contain explosive means for separating the first stage motor ll and the skirt section 15 from the remainder of the missile system. Forwardly of the second stage motor I3 is an equipment section 16 to which a ballistic missile or re-entry body 17 is detachably connected by the separation means, the nose of the reentry body being provided with a nose fairing 18. It will be understood, of course, that the several components of the missile system are adapted to be connected together and that the equipment section 16 houses suitable guidance and control mechanisms operatively connected to the propulsion controls and separation means for guiding the system along the proper booster trajectory or flight path and for separating the portions of the system as is necessary for delivery of the missile component or re-entry body 17 on the intended target.

Turning now to FIG. 2 for a better understanding of the flight of the missile system and the function of the separation means of this invention in such flight, the missile system is shown as being ejected from a submerged submarine 19', although, of course, it could be launched from a surfaced submarine, surface vessel, or from dry land, if desired. Timed with the launching of the missile system is the ignition of the first stage motor 11 as at A in FIG. 2.

Upon burn-out of the first stage motor 11, first separation is effected as at B, FIG. 2. Such separation can be effected by a loop of Primacord 21 disposed within the skirt section 15, FIG. 1, the Primacord being detonated at the proper time by control mechanisms in the equipment section 16 which are responsive to the burning out or tailoff of the motor 11.

After this first separation, the first stage motor 11 falls and the second stage motor 13 continues on its guided trajectory to a point where the velocity and the direction of the re entry body are such that, if free from the second stage motor, the ballistic missile or re-entry body 17 would follow a ballistic trajectory intersecting the target. At this point, C in FIG. 2, second separation and thrust termination occur in response to appropriate signals from the control mechanisms in the equipment 16. After separation at point C, the second stage motor 13 and attached equipment section fall away from the re-entry body 17 which continues on its unguided or ballistic trajectory to target T.

The upward flight of the ballistic missile or re-entry body 17 carries it though the outer reaches of the earth's atmosphere and beyond the mesosphere. The nose fairing 18 is provided to protect the nose of the reentry body 17 during passage through the lower, thicker regions of the earths atmosphere. Prior to reentry of the ballistic missile 17, nose fairing 18 is forced off or jettisoned in response to ambient conditions in the upper rarefied atmosphere, as at D in FIG. 2, the nose fairing being needed only for the upward flight and unnecessary during re-entry because of the design of the re-entry body.

It will be appreciated that after second separation the ballistic missile 17 is no longer powered or guided and that if deflecting forces were exerted upon the re-entry body it could be caused to depart from the intended ballistic trajectory. It is therefore important at second separation that such deflecting forces be absent or be minimized so that the ballistic missile will proceed to the target. Thus, the second separation must be as smooth as possible. The separation means of the present invention is designed to effect smooth separation of the ballistic missile from its propulsion means.

For a detailed description of the separation means of the present invention, reference is made to FIG. 4 showing a cross sectional view generally in the plane of the joint between the equipment section 16 and the reentry body 17, that is, generally along the line 4-4 of FIG. 3. Equipment section 16, in the form of a frustum of a cone, is forwardly terminated by an annulus or annular member 22 having the cross section shown in FIG. 5 and providing an outvw. .ll faced opening. At spaced intervals around the circumference of the annulus 22 there are formed openings 24 through which studs 25 secured to the re-entry body protrude, see FIGS. 5 and 6. Each of the studs 25 has a notch on the side thereof facing outwardly and has a sloping surface 26 oppositely disposed with respect to a surface 23 of annular member 22, see FIG. 6.

Associated with the annulus 22 and studs 25 is a segmental locking band 27 comprising three segments 28 and the associated interconnecting means 29. Each of the interconnecting means 29 may take the form of a pair of T-

bolts

31 and 32 connected to the adjacent ends of segments 28 and a turnbuckle 33. The ends of the segments 28 are suitably formed to be engaged by the T-bolts as is well known in the art and need not be further described.

The intermediate portion of each segment 28 is formed with a pair of

sloping surfaces

34 and 35 complementary to and adapted to engage with

surfaces

23 and 26, respectively. Thus, it will be seen that as the turnbuckles 33 are turned to draw the associated T- bolts together, segments 28 will be drawn into a tighter relation with respect to annulus 22 and studs 25 with the result that

surfaces

34 and 35 will slide along

surfaces

23 and 26 causing them to spread and bring the re-entry body 17 into a secure relationship with the equipment section 16. For the purpose of providing an airtight seal between the re-entry body 17 and the equipment section 16 there is provided an O-ring 36 disposed in a groove in the annulus 22.

It will be noted that the flare of the equipment section 16 is a continuation of the flared portion of the reentry body 17 and, in order to provide a smooth surface, the outwardly facing opening of the annulus 22 is covered by a fairing strip 37 formed in segments and provided with a plurality of spring clips 38 having fingers gripping the

surfaces

34 and 35 of the associated locking band segments 28, see FIG. 7.

Portions of the annular member 22 are cut away as necessary to admit the spring clips 38 and the ends of the segments 28 and associated interconnecting means 29.

Each of the segments 28 is made of spring steel and tends to assume a straight line position. Hence, when the segments 28 are tightened into the bent positions shown in FIG. 4, they are placed under stress whereby upon release of the interconnecting means 29, the segments will tend to fly out from engagement with the studs 25 and annular member 22 thereby effecting separation of the re-entry body 17 from the equipment section 16. The space inwardly of the joint between the re-entry body and the equipment section is filled with air or any suitable gas under a pressure of about 12 psi with the result that when the interconnecting means 29 are ruptured for release of the segments 28, which occurs at a high altitude where the atmospheric pressure is quite low, the pressurized air or gas forces the reentry body 17 away from the equipment section 16.

In FIG. 8 there is shown one form of explosive actuated means 39 for rupturing or fracturing the interconnecting means 29. The explosive actuated means 39 comprises a tubular housing 41 connected to a plate 42 which is secured to the equipment section 16 in any suitable manner, as, for example, by bolts. The housing 41 contains a slug 43 which is aligned with the turnbuckle 33. The housing 41 is adapted to receive an electrically fired squib 44 containing explosive 45, the detonation of which serves to drive the slug 43 against the turnbuckle 33 for fracturing the same. The fracturing of the turnbuckles 33 releases the interconnecting means 29 and the segments 28 of the locking band. Incident to the release of the interconnecting means 29, adjacent portions of the segments of the fairing strip 37 will also be ruptured and the segments of the fairing strip will fly out with the associated segments 28 of the locking band. The adjacent ends of the segments of the fairing strip may be interconnected by providing a backing strip 46, as shown in FIG. 8, secured to one end of a fairing strip segment and disposed in undcrlapping relation to the adjacent end of another fairing strip segment and fastened thereto by a bolt 47, or the like.

In the embodiment of FIG. 9, the explosive means is incorporated in the interconnecting means. In this form of the interconnecting means. which is designated generally by reference numeral 49, there is provided a hollow housing 51 having integrally formed therewith a T- portion 52 at one end thereof. Housing 51 is formed with

coaxial bores

53 and 54 of different diameters and a shoulder 55 therebetween, bore 53 being located adjacent T-portion 52 and bore 54 being threaded. Externally, housing 51 is provided with a circumferential groove 56 encompassing bore 53.

A spacer block 57 is seated against shoulder 55 for closing off bore 53, thereby forming a chamber for an explosive mixture 58. The explosive mixture 58 may be detonated by any suitable means such as, for example, electrical wires 59 extending through a bore or channel 61 in T-portion 52. Also received in bore 54 is a tubular lock nut 62 having outer threads engaging the threads of bore 54 and inner threads engaging a T-bolt 63.

Although the device of H6. 9 is not shown connected to segments 28 of the locking band 27, it is obvious that such device may replace

elements

31, 32 and 33 of FIG. 8. The device of Flg. 9 is so proportioned and related to the segments 28 that when lock nut 62 has been tightened to hold the spacer block 57 against shoulder 55, T-bolt 63 may be drawn toward T-portion 52 sufficiently to provide the desired tightness of the segments 28 of the locking band 27. When the device in Flg. 9 is used in lieu of

parts

31, 32 and 33 of FIG. 8, the need for the explosively actuated means 39 is eliminated and means 39 therefore may be omitted.

The operation of the device of FIG. 9 is similar to that of the device of FIG. 8 in that upon receipt of the proper electrical impulse, explosive mixture 58 is detonated, thereby causing rupture of the housing 51 in the area of the groove 56 for forcing apart each T-portion 52 and T-bolt 65. This releases the segments 28 of the locking band 27 for separation of the re-entry body 17 from the equipment section 16.

Briefly summarizing, rupture or fracture of the means interconnecting the segments 28, whether such means comprise turnbuckles 33 (FIG. 8) or housings Sl (FIG. 9), serves to release the segments 28 which tend to assume straight-line unstressed conditions and fly outwardly from

surfaces

23 and 26 on annular member 22 and studs 25, respectively, thereby permitting re-entry body 17 to separate from the equipment section 16 smoothly and with very little or no vibration. A volume of pressurized air or gas between the equipment section and the re-entry body assists and assures such separation.

Obviously, many modifications and variations of the present invention are possible in light of the above teachings. It is therefore to be understood that within the scope of the appended claims the invention may be practices otherwise than as specifically described.

What is claimed is:

1. In a missile of the type having a ballistic missile component and a booster motor adapted to propel the missile component during the boost phase of its trajectory, the booster motor having a forward section and the missile component being disposed so as to coextensively abut the forward section, the improvement comprising; an annular member secured to the forward edge of said section and extending inwardly thereof. said member having an outwardly facing recess, a plurality of studs disposed inwardly of said missile component and affixed thereto, said studs having indented portions projecting into and being at least in part contiguous with said recess, a locking band, and releasable means holding a locking portion of said band tightly within said recess and against said indented portions for securely connecting said missile component to said section.

2. A missile as set forth in claim 1 wherein the locking band comprises a plurality of segments interconnected by releasable members.

3. A missile as set forth in claim 2 wherein said releasable member includes an explosive element for effecting the release thereof.

4. A missile as set forth in claim 3 wherein said segments of the locking band are of spring metal, said releasable members holding said locking band segments in a curved manner so that upon explosion of said explosive element rupturing said releasable members the bands will straighten.