US2608931A

US2608931A - Rocket

Info

Publication number: US2608931A
Application number: US651299A
Authority: US
Inventors: Charles C Lauritsen
Original assignee: Individual
Current assignee: Individual
Priority date: 1946-03-01
Filing date: 1946-03-01
Publication date: 1952-09-02
Anticipated expiration: 1969-09-02

Description

Sept.' 2, 1952 c. c. LAURrrsEN ROCKET Filed March 1, 1946 INVENTOR ATTORNEY m n R w c. ...m M m Patented Sept. 2, 195,2 :iran-.1:1

ROCKET Charles C. Lauritsen, Pasadena, Calif., assigner to the United States of America as represented by j .the Secretary of the Navy Application March 1, 194s, serial No. 651,299

s ciaims. (c1. 1oz-919) This invention relates "to -rocket projectiles and has particular relation torockets provided with a head structure containing anexplosive and afuze responsive to ypressures generated by burning'of the propellant in the motor tube.

lAlthoughuse `of the invention is not limited to any particularrocket projectile, it has found particular use in rockets of the type disclosed in copending application Ser. No. 652,439,` assigned to the same assignee as is the present invention. f f H Y 1 i ne object of the inventionis Vto provide a rocket whichis capable of carrying as a pay load any one ofY several types of head structures closely resembling in function and operation the various gun projectiles such asfragmentation, armorpiercing,l chemical shells etc'.and which may employ either or both nose and base fuzes.

Another object of the invention 4is tof provide a rocket which provides' a simpleand effective means of detachably connecting the motor tube and the pay loador head structure.

`Afurther object of the inventionis to provide in 'a rocket projectile having a nose or` war head structure containing a pressureoperated fuze, means fordetachably mounting the head structure onto the motor tube, and means for normally sealing the motor tube from the head structure, `said means beingv rupturable uponburning of the propellant for exposing the` fuze` to the pressure of the propellant gases.

In amplification of the latter statement, it is an important object of the-invention to( provide a combined sealing andrupturable diaphragm which seals the end of the rocket motor tube opposite to the nozzle against the access of moisture to the propellant charge during storage and shipment, and ruptures to permit the escape of pressure gas either in the event of the inadvertent ignition of the propellant charge during storage and shipment,or to permit said escape to actuate the fuze of the ultimately attached war head when the projectile is in night.

These and other objects of the invention will be better understood by reference to the following description and accompanying drawing, in which The single figure is an elevational view of a rocket incorporating a preferred embodiment of the present invention, with portions thereof broken away and in section.

Referring to the drawing, the rocket includes a motor tube I which is internally threaded at its forward end ll to support a nose or head structure I2 which functionally may be similar to a fragmentation, armor-piercing or chemical shell etc. The head structure has` a' rearten'd portion I3 of reduced diameter which slips Within the forward end ll of the motor tube I0 and is threaded for attachment thereto'as at I4. `The head structure is provided with a suitable nose fuze i5 which may be conventional, and the base end is provided with a base fuze i6 prefer#- ably of the type shown in copending application Ser. No. 576,119, assigned to the same assignee as is the present invention. Fuzes of this type are designed to be armed bythe pressuregen- .erated in the rocket motor:

The rear end i3 of the head structure `is positioned within the motor tube l0 which is lclosed by a diaphragm 20 securedaroundits rim to the interior wall of the motor tube. The diaphragm is mounted between felt packing washers 2 l and 22. The Washer 22 `is carried by the diaphragm"- For this purpose use is made of the centrally located annular flange I7 which, because of being erected from the diaphragm 20 toward the burnable charge 24, provides a shoulder on which the washer is fitted in contact with the diaphragm and said charge. The edge of this flange is turned inand has'the .periphery of the disk 23 crimped upon it. The diaphragm 20 has a central open# ing in which a blow-Out disk 23 is fltted tightly as indicated but is adapted to'give .way when a predetermined pressure is generated in` the rocket motor in order that this pressure be` available to arm the base fuze i6. An additional purpose of the rupturable diaphragm, in other"words the diaphragmv 20 with its blow-out disk 23:, is to (l) seal the motor 'tube l0 Vduring?shipment and (2) provide a relatively safe gas escape in case of an inadvertent detonation of the igniter 24 and consequent ignition of the powder grain 2l. Adjacent the diaphragm 2li is an igniter 24 comprising a case containing one or more electrical squibs (not shown) and a charge of ignition powder such as black powder. The squibs are connected to a source of electrical current by means of the terminal 25 and the conducting wires 26 which lead out the rear end of the motor tube. The remaining portion of the motor tube is iilled with a propellant grain 21 preferably in the form of a single extruded member, in this case of cruciform cross section. It will be noted that the packing washers 2l and 22 tend to compensate for variations in length of the propellant charge caused byrchanges in temperature.

The rear end of the motor tube is closed by a suitable nozzle arrangement (not shown), preferably of the construction disclosed in copending of the type generally known as zero-length 'isemployed, inasmuch as with such a launcher the rocket acquires full flight after moving only a nominal distance. For cooperation vwith Vsuch .a launcher. the rocket is provided with a forward button lug 3| and a rearward loop strap 32.

In operation, the rocket, if fired from a mov ing aircraft, is suspended from the launcher by The invention herein described may be manufactured and used by or for the Government of the United States of America for governmental purposes without the payment of any royalties thereon or therefor.

I claim:

1. In a rocket projectile having a motor tube containing a ypropellant "andlga headjstructure de- -tach'ably mounted there'nfsa'idl headstructure containing an explosive and having a fuze ac f. ,-table by pressure of propellant gases from said .motor tube on ignition of said propellant; means 'for assuring sealing of said motor tube in the possible absence of the head structure, said means comprising aediaphragm secured to the motor tube,` separating said propellant from said head i structure and having an opening therein, and a means of the lug 3l and strap 32. The "x'rires'2i,v l

which lead out the rear end of the rocket, are connected to a source Aof `electrical current (not -HhQWnL The electrical current ignites the squib orfigniter 24 which linitiates combustion of the propellant grain 2L When the generated gases reach a :predetermined pressure, the blow-'out disk 2311s ruptured thereby exposing the pres#` sure operatedbase `fuze IB to the propellant gases whereby the base fuze I6 `is actuated to detonate ya. r1,explosive in the war head I2 or armthe nose .f-uzeffli, Y i

Y v-.Ift-will be vapplrerii, that the warhead I2. is readily detachable from the motor tube l0 -without exposing the propellant grain 2'! to moisture or. -ignitionhaZa-rdS; that is, the propellant grain v remains sealed during an interchange of war -mediately so that lburning w-illv not b'e sustained.

It will also be apparent tha-tithe blow-out disk 2 3 may be s o constructed as to withstand ac-` cidental ignition'of the igniter 2 4 and yet submit to fracture by the pressure of Athe propellantgases.

inthe event'that the igniter fails to ignite thefpropellant, the blow-out disk will prevent .pree gnature actuation of the b'ase fuze. In addition. theblow-out diskmay be constructed so as not to be ruptured Mby pressuresV :caused by a partial burnns'of the propellant grain. f

blow-out disk normally sealing said opening and adapted to be ruptured by said gases to establish communication betweensaid motor and said fuze upon ignition off-said propellant. L j,

2gfIn a rocket projectilehaving a otorjtgube containing Ya burnableV chargeconirontignga `jet nozzleatzone end.; -a'safety .accessoryat thezother end ,of theV 'tube primarily eieetive during the v .storage and shipment of the motortubeca-Dd its contained charge, said accessory comprising a sealing :diaphragmlocatedinteriorly Of and across the tube and securedfaroundits rim to the interior wall of `the tubefand-.agrupturable portionmade integral with the diaphragm to be partfofjthe seal, saidl portion blowing out in cned-irectio'n simultaneously -wthz-the blowing nftheigas iet at the nozzle case-'of inadvertent ignition of said charge. j .5 u

3'. lIn a'rock'et projectile havinga `inciter; tube containing a` burnable 'eharge; 5 Y a vsealing d-I; aphragm. :across thev interior of the tube at 'one end offsaid charge and having a rupturableportion, an 'annular 4iiangeierected jffrom 'the dif aphragm toward the gchargey-.providing-a shoulder and carryingsaid -rupturable:portiony vand .aj :com: pressible-washer' surrounding :the rupturablez-portion and `being mountedv on the shoulder in; cori-f` tact'withthe diaphragm and burna-ble charge v f 'C-.QLAURIYTSE'N v f REFERNCS'QITEp n J The renewing references are' 'or record `in :th fue of thisv-p'fauaent:H t Y f- UNITED STATES' Number :Name -7 'zgatefkl; 251,455.07 Denoix gg 1Jan.31f, 4939