US2809584A

US2809584A - Connector ring for two stage rockets

Info

Publication number: US2809584A
Application number: US346291A
Authority: US
Inventors: Smith Bernard
Original assignee: Individual
Current assignee: Individual
Priority date: 1953-04-01
Filing date: 1953-04-01
Publication date: 1957-10-15
Anticipated expiration: 1974-10-15

Description

Oct. 15, 1957 B. SMITH CONNECTOR RING FOR TWO STAGE ROCKETS Filed April 1, 1953 IN V EN TOR.

mg M M/Wm jg United States Patent 2,809,584 CONNECTOR FOR TWO STAGE ROCKETS Bernard Smith, Inyokern, Califi, assignor to the United States of America as represented by the Secretary of the Navy j Application April 1, 1953, Serial No. 346,291 Claims. (CL 102-49) (Granted under Title 35, U. S. Code (1952), sec. 266) the members.

to be positively forced apart when the booster component separates from its forwardly attached component.

Another object is to connect the segments of the connector ring with explosive bolts.

Another object is to provide a plurality of connector ring segments, connected by a plurality of explosive bolts, which segments may articulate with respect to unactuated bolts and separate from a booster when only one of the explosive bolts is actuated.

Another object is to provlde an improved detachable connection between a booster component and its forwardly attached unguided component which permits sep aration of the components without applying lateral course deflecting forces to the forwardly attached component during separation, to thus ensure against trajectory disturbances of the latter.

Another object is to provide an-improved connection between a booster component and a missile providing a maximum degree of reliability and positiveness in its releasing function.

Other objects and many of the attendant advantages of this 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. 1 is a section taken on line 1-1, Fig. 2;

Fig. 2 is a side elevation of Fig. 1, portions being shown in section taken on line 22;

Fig. 3 is an enlarged section taken on line 33, Fig. 1, and

Fig. 4 is an enlarged section taken on line 44, Fig. 2. 7

Referring in detail to the drawing, the invention comprises in general, a connector ring and joint 10 which detachably secures the forward end of a booster rocket motor 11 to the rear end of a rocket 12, the rear end of.

the latter being illustrated as an exhaust nozzle 13.

Booster 11 may be of any well known type motor to which is secured at its forward end a circular ring 14 having a planar front face 15 disposed in abutting relation to planar rear face 16 of a similar ring 17 forming an integral part of the rear end of nozzle 13. An annular pilot 18 extends forwardly from ring 14 and telescopes within the bore of nozzle 13, preventing relative lateral movement between booster 11 and rocket 12. The rear face 19 of ring 14 and the front face 20 of ring 17 taper toward each other in an outward direction, as best shown in Fig. 3.

The connector ring 21 comprises three identical arcuate segments 21a, 21b, 210 which are channel shaped in cross section, each having confronting

inner faces

22, 23 which are tapered to fit

faces

19, 20, respectively. Outwardly projecting lugs 24 are afiixed, as by welding, to each segment near opposite ends thereof, each lug having an aperture 25 extending therethrough which receive portions of the explosive bolts to now be described.

As best shown in Fig. 4, each explosive bolt 26 comprises a member 27 having a cylindrical bore 28 therein, and a cylindrical piston member 29 which slideably fits within bore 28, but is prevented from unauthorized sliding movement by a shear pin 30 extending between Each of the aforesaid members is .provided with a threaded shank portion 31 extending through an enlarged aperture 25'which threadedly carries a nut 32 having a spherical face 33 which abuts a mating spherical seat on a lug 24. The construction just described provides joints between adjacent segments which permits articulation of the latter in the plane of the connector ring. An aperture 34 extends axially between opposite ends of the explosive bolt, and is internally threaded adjacent the ends thereof for threadedly re-' ceiving plugs 35.

Electric wires

36, 36 extend through each plug and connect with independent bridge wires (not shown) of a pair of

conventional squibs

37, 37 which are adapted to either singly or conjointly ignite gun powder 38 contained in a tubular paper cartridge 39, the gun powder forming a charge, which upon detonation, forces the members of the explosive bolt apart, which in turn, positively force adjacent segments apart. This construction provides for the contingency that in event all of the explosive bolts should fail to detonate, except one, due to a faulty circuit or otherwise, the bolts which fail to detonate provide the articulated connections, previously referred to, which permit relative movement be tween adjacent segments and permit the connector ring to clear the flanged joint and thus jettison to permit release of the booster motor from the forwardly attached missile.

In the use of the device, the booster motor and rocket are clamped together in the position illustrated, the final operation after clamping being the insertion of the powder cartridges in the axial apertures in the explosive bolts and the plugging of the ends of the apertures with the threaded plugs. After launching and during the flight of the combined missile the booster will expend its propulsive force at which time suitable apparatus, well known in the art, will ignite the squibs in the explosive bolts. This ignites the powder and the high pressure developed within the bores of the bolts effects relative movement between their piston and cylinder members, shearing the shear pins, and positively forcing adjacent segments of the connector ring away from each other and freeing the segments from the

adjacent rings

14, 17 on the booster and rocket. The booster and ring segments fall free of the rocket and the rocket continues on its mission under its own propulsion charge which is ignited at the time of separation by suitable apparatus well known in the art.

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

What is claimed is:

1. In a separable missile of the type having a booster motor adapted to propel the missile during the booster period of its trajectory and a rocket adapted to be self propelled after the booster motor is separated therefrom, the rocket and booster motor being disposed in tandem relation with the latter behind the former, the improvements comprising; a pair of outwardly extending annular flanges, one rigidly aflixed to the rear end of the rocket and the other rigidly affixed to the front end of the booster motor, the flanges having juxtaposed abutting faces, an internally grooved ring formed of a plurality of segments adapted to engage the flanges, and a plurality of explosive bolts connecting adjacent segments in clamping engagement with the flanges preventing separation thereof, each bolt comprisingseparable members, one member being aflixed to one segment and the other member aflixed to an adjacent segment, and an explosive charge carried by each bolt adapted to produce gas under pressure to bodily separate its separable members,

2. Apparatus in accordance with claim 1 wherein the separable members of each bolt include a cylinder forming a portion of one member and a piston forming a portion of the other member, the piston being disposed within the cylinder, shearable means preventing relative movement between the piston and cylinder, the explosive charge adapted to produce gas under pressure in the cylinder for shearing the shearable means and eifecting movement of the piston and cylinder in opposite directions.

3. Apparatus in accordance with claim 2 including an aperture extending axially of the piston and cylinder and between opposite ends of each bolt, the explosive charge being disposed within the aperture, removable plugs adapted to close both ends of the aperture, and electric wires extending through each plug.

4. In a separable missile of the type having a booster motor adapted to propel the missile during the booster period of its trajectory and a rocket adapted to be self propelled after the booster motor is separated therefrom, the rocket and booster motor being disposed in tandem relation with the latter behind'the former, the improvements comprising; a pair of outwardly extending annular flanges, one rigidly aflixed to the rear end of the rocket and the other rigidly aflixed to the front end of the booster motor, the flanges having juxtaposed abutting faces, an internally grooved ring formed of a plurality of segments adapted to engage the flanges, outwardly projecting lugs disposed adjacent ends of the segments forming spaced pairs of lugs for securing ends of adjacent segments together, substantially tangentially disposed apertures extending through the adjacent pairs of lugs, and an explosive bolt disposed between lugs of each pair, each explosive bolt comprising separable members, each member having a shank portion extending through an aperture in a lug and a nut on the outer end thereof engaging the lug through which it extends adapted to draw adjacent lugs toward each other to thereby clamp the segments on the flanges, portions of the members disposed between the lugs including a cylinder forming a part of one of the members and a piston forming a part of the other member, the piston being disposed within the cylinder, shearable means preventing relative movement between the piston and cylinder, and an explosive charge carried by the bolt adapted to produce gas under pressure in the cylinder for shearing the shearable means and eflecting movement of the piston and cylinder in opposite directions.

5. Apparatus in accordance with claim 4 wherein the apertures in the lugs are of a size to permit adjacent segments to articulate relative to the shanks of a connecting bolt and each nut is provided with a spherical surface engaging a mating spherical surface on the associated lug, the construction and arrangement adapted to permit the ring to disengage from the flanges when only one bolt is actuated by its explosive charge.

References Cited in the file of this patent UNITED STATES PATENTS 2,479,580 Marco a Aug. 23, 1949 2,485,921 Rockwell Oct. 25, 1949 2,539,643 Smythe Ian. 30, 1951 2,556,672 Bergh et al June 12, 1951