US3167018A - Missile safety and arming circuit - Google Patents

Missile safety and arming circuit Download PDF

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US3167018A
US3167018A US180533A US18053362A US3167018A US 3167018 A US3167018 A US 3167018A US 180533 A US180533 A US 180533A US 18053362 A US18053362 A US 18053362A US 3167018 A US3167018 A US 3167018A
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missile
contacts
acceleration
relay
switch
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US180533A
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John E Brunner
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Aeronca Manufacturing Corp
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Aeronca Manufacturing Corp
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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42AMMUNITION; BLASTING
    • F42CAMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C19/00Details of fuzes
    • F42C19/06Electric contact parts specially adapted for use with electric fuzes

Description

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.m .mm 7 W T. 7 a www: Y \\M m f 6 J V Vl 1, n. ww m i T N T. f m uw R. mm n. Q ,M u 2 @u my M W mnu w m m w a B T Jv E m m i m ms F d J u m x Q Q E F u m M ww N1 5 QN 1 f. Q e, J \|J| 1 m w S J ww wQQl 3,167,018 Patented Jan. 26 1965 3,167,0i8 MSSILE SAFETY AND ."1 'l`-. CIRCUIT John E. Brunner, Middletown, Ohio, assignor to Aeronca Manufacturing Corporation, Middletown, Ohio, a corporation of Ohio Filed Mar. 19, 1952, Ser. No. 180,533 5 Claims. (Cl. IGZ-70.2)

The present invention relates to missile control circuits and is particularly directed to a missile safety and arming circuit for preventing actuation of various missile components until after a missile has been properly launched.

Many missiles in operation today include various explosive or pyrotechnic devices which are utilized at various points in the missiles flight to cause the missile to perform certain predetermined functions. For example, in many missiles explosive means are provided for forcibly separating missile sections following the burn-out of the missile motor or rocket. Many missiles also carry iiares which are ignited during the missile flight to facilitate optical or infrared tracking of the missile. premature actuation of these devices during shipment or pre-launch operations, or in the case of a defective launch canV result in injuries in personnel as well as damage to the missile. Thus, the primary function of the missile safety and arming circuit is to prevent actuation of any of these devices until the missile has been properly launched.

The present invention is predicated upon the concept of providing a missile safety and arming circuit comprising the combination of an acceleration responsive electrical switch and a thermal time delay element which cooperate to arm the missile only after the missile has undergone a predetermined acceleration for a preset time. Or Viewed somewhat differently, the present arming system obtains a time integral of acceleration and in effect arms the missile only after it has reached a predetermined velocity indicating that the missile has been properly launched. l

More particularly, in one preferred form of missile embodying the present invention, control over the various missile components is maintained by a programmer powered by a battery or other power source carried by the missile. The present arming system controls energization of the programmer motor so that the programmer is actuated only after the missile reaches a predetermined velocity.

' The present missile safety and arming circuit comprises an acceleration responsive switch having normally open contacts in series connection with a secondary power source, a current limiting, or time delay, resistor, and the fuse wire of a current-sensitive thermal relay. The thermal relay in turn has normally open contacts in series connection with the programmer and its source of power.

In operation, the acceleration switch which is a simple mass spring type of accelerometer is closed as long as the missile is undergoing an acceleration in excess of a predetermined value. When this acceleration switch is closed, current is applied to the fuse wire of the currentsensitive thermal relay. This device functions somewhat like a fuse in that the fuse wire is effective to hold the contacts of the relay open until a predetermined amount of electrical energy is applied to the fuse links causing them to melt. vWhen the fuse links do melt, they release a contact arm which moves under a spring force to close the programmer energization circuit. By way of example, in one embodiment these fuse links require a predetermined current flow for two seconds before the fuse links melt to cause closing of the current-sensitive thermal relay contacts.

Thus, when a missile is fired and reaches a predetermined acceleration, the accelerometer switch closes completing a circuit through the current limiting resistance example if the missile were jarred or in the event of a faulty launch, the current flow to the fuse wire of the It is apparent that any K current-sensitive thermal relay is not suicient to melt the fuse links so that the programmer is not energized. Then, when the acceleration switch subsequently reopens current ilow to the thermal relay stops so that the relay is not closed and the programmer is never energized.

One advantage of the present missile safety and arming circuit is that it is extremely simple and is considerably more reliable than previously suggested arming circuits utilizing mechanical devices such as escapement mechanisms and the like. The only moving parts of the present unit are the mass carried contacts of the acceleration switch and the spring urged contacts of the thermal time delay element. As a result, the operation of the present circuit has a high degree of reliability even under extremely adverse environmental conditions of shock, vibration, temperature and the like.

Another advantage of the present arming system is that despite its high reliability, it is lower in cost than mechanical systems which require relatively complex and intricate mechanical components.

Still another advantage of the present invention is that the thermal time delay relay is a very small component which is approximately the size of a small fuse. This ele- `ment can be removed from the system during shipment of the missile and can be readily inserted during the final launch operations. Obviously with this element removed from the system it is absolutely impossible to arm the missile irrespective of any shock loads to which the missile might be subjected during transport and set-up for launching.

These and other objects and advantages of the present invention will be more readily apparent from a consideration of the following detailed description of the drawings illustrating a preferred form of the present invention.

In the drawings: FIGURE 1 is an elevational view of one form of missile embodying the arming and safety circuit of the present invention.

-FIGURE 2 is a schematic circuit diagram of an arm- 5 ing and safety circuit of the present invention.

FIGURE 3 is a longitudinal cross-sectional View through one preferred form of current-sensitive thermal relay.

One form of missile 10 with which the-.present arming and safety circuit can be used is illustrated in FIGURE l. It is to be understood that missile 10 is merely exemplary and that the present arming and safety circuit can be utilized with many other different types of missiles. As is shown in FIGURE 1, the missile 10 comprises an afterbody section 11 which houses a solid fuel rocket propellant motor. The missile further comprises a nose section 12, an electronics bay 13, a parachute receiving bay 14 and a separation section 1S.

This missile is particularly adapted for use as a target missile. In one use of the missile, for example, it is fired to a predetermined altitude for example one hundred thousand feet. The missile is then supported by a parachute for a slow descent while the missile emits electromagnetic radiations suitable for tracking by ground to air or missile-to-missile tracking devices. The missile nose section 12 also house infrared flares which are ignited during flight to provide targets for infrared tracking devices. During the normal ilight of such a missile, several explosive devices are actuated in addition to pyrotechnic devices such as the infrared flares carried in nose section 12. Thus, for example, one explosive charge is ignited in separation section 15 to cause afterbody section i1 toV be separated from the remaining portions of the missile.-

A second explosive charge is ignited at the juncture of nose cone 12 and electronics bay 13 to cause the nose cone to be blown away from the remaining portions of the missile. Still other explosive squibs are actuated to perform such functions as severing reeing lines', and the like.

Actuation of the various component elements of the missile is controlled by a programmer 16. The exact details of construction of the programmer 15 constitute no part of the present invention. However, in general, it can be stated that the programmer comprises a motor adapted to be energized from a primary power source, such as battery 17, through a circuit including leads 18 and 20, normally open contacts 21 and 22 of a current-sensitive thermal relay 23 and a lead 24 which interconnects one terminal of battery 17 to contact 22. The motor of programmer 16 drives a plurality of cams which in turn actuate various switches to complete circuits to the various explosive charges and squibs in a predetermined time sequence following actuation of the programmer.V Both the programmer 16 and the missile arming circuit indicated generally at 25 are mounted within electronics bay 13.

The missile arming and safety circuit is shown diagrammatically in FIGURE 2. As is there shown, the safety and arming circuit comprises an acceleration responsive switch 26, a resistance 27, current-sensitive thermal relay 23, and a secondary power source, such as batteries 28. More particularly, acceleration switch 26 is a conventional acceleration type of switch of the mass spring type. That is, switch 26 comprises a compression spring 30 which normally retains a mass 31 in a retracted position. Mass 31 carries a contact bridging arm 32 which is normally spaced from two stationary contacts 33 and 34. Contact 34 is connected to one terminal'of battery 28 through a lead 35, while contact 33 is joined through lead 36 and resistor 27 to one terminal 37 of re-j lay 23. Another lead 38 interconnects a ksecond terminal means of a generally VU-sl'iaped fuse'wire 51. This fuse wire is looped around a transverse pin 52 extending across a rearwardly opening bore formed in plunger 44. The free ends of fuse wire 51 are looped over as at 53 and 54 for engagement with stationary loop members 55 and 56 carried by rear header assembly 5t). When the thermal 4 relay is assembled the fuse wire is effective to hold the plunger 44 in its retracted position with contact face 45 spaced from stationary contacts 21 and 22. This is the position shown in FIGURE 3. However, as soon as fuse wire 51 melts, spring 48 is effective to shift the plunger 44 forwardly to bring the plunger nose 46 into bridging con- Y tact with stationary contact terminals 21 and 22. TheV 40 of relay 23 to batteries 28. It is to be understood that switch 26 is mounted within missile 10 so that Wall 41 of the missile faces forwardly, i.e., faces nose-section 12. Thus, when the missile is accelerated, the Vinertia 0f mass 31 tends to retard movement of the mass relative to the missile and stationary contacts 33 and 34. Thus, the mass 31 acts against the force of spring 30 and contact arm 32 is brought into bridging relationship with station ary contacts 33 and 34.

Details of construction of one suitable form of currentsensitive thermal relay 23 are shown in FIGURE 3. These relays are commercially available from Thermocal Division of Jamieson Laboratories, Inc. and are sold under the trade name Pyristor; other similar relays are available from Networks Electronic Corporation. As is shown diagrammatically in FIGURE 3, the relay 23 includes a housing 42 which hermetically seals the remaining elements of the relay. The relay comprises two rigid stationary contacts 22 and 21 which are carried by a header assembly 43. These contacts are normally spaced from a retractable plunger 44. The plunger includes a forward face 45 from which extends a conductive bullet shaped nose member 46. The shape of thismember insures that the plunger enters between contacts 21 and 22 Plunger 44 is normally held in a retracted position by overall physical size of one suitable thermal relay of this type is approximately an inch in length and a quarter of an inch in diameter. YIt will, of course, be appreciated that relay housing 42 is thermally insulated to substantially eliminate environmental temperature effects.

In the present missile and arming circuit 25 the components are interrelated so that the size of resistor 27 in relation to the potential of secondary power source 28 and the capacity of fuse wire 51 is such that fuse wire 51 burns out when current flows through it for a predetermined time, for example two seconds, although obviously by. changing the resistor size a longer or shorter time'could be required.

Iny operation, thermal-relay 23 is placed in the arming circuit only during the iinal launch preparation. Since the relay contacts 21 and 22 are normally open, the programmerV motor is deenergized and circuits cannot be completed to any of the devices controlledby the programmer. After the missile has been launched, the acceleration switch 26 closes its contacts 33 and 34. Thus, a circuit is completed from secondary power source 28 through resistor 27 and leads 38 and 36, to terminals 37 and 40 of the `thermal relay 23. Current ows from these terminals through fuse wire 51. Y Y

Assuming that the missile has been properly launched and that the acceleration continues for in excess of the preset time, two seconds in this example, the fuse wire is heated to aV point where it melts. Thus, plunger 44 is released to move forwardly under the action-of spring 48. When Ythe plunger moves forwardly, nose member 46 bridges the stationary contacts 21 and22 of the relay.

A circuit is thus completed through these contacts from has no further control over the thermal relay or pro-` grammer. Thus, when'that switchY opens it does not in Vany Way effect operation of the programmer. However,

in the event of a faulty launch in which the acceleration is initiatedY to originally close switch 26, but does notrlast for a proper time, switch 26 momentarily closes to cause a current to flowthrough fuse wire 51. However, current does not flow for a sufficient length of time to cause the fuse wire to melt so that the plunger `44 is never released and the missile programmer is never placed in-operation.

From the foregoing. disclosure of the general prinj ciples of the present invention and the above detailed description of a preferred embodiment, those skilled in the art will readily comprehend various modifications of which the present invention is susceptible. Accordingly, I desire to be limited only bythe scope of the following claims. Y Y i Having described my invention, IY claim: Y.

. l. A missile safety and arming circuit foi-'. a missile including a programmer, said circuit comprising an acceleration responsive switch of the mass-spring type having normally open contacts andincluding means for closing said Vcontacts'whe'n said switchis subjected to a predeterminedl acceleration and reopening said contacts in the event said switch is closed in response to said predetermined acceleration and is subsequently subjected to an acceleration less than said predetermined acceleration, an electrical current-sensitive thermal relay having a fuse element, a rst source of potential, a resistor means interconnecting said rst source of potential, said resistor, said acceleration switch contacts, and said fuse element of said relay in series electrical connection, said relay having a pair of normally open contacts, a power source in series electrical connection with said relay contacts, and means interconnecting said power source and said relay contacts with said programmer, whereby said fuse element melts to energize said programmer only after said acceleration responsive switch is closed for a predetermined time.

2. A missile arming and safety circuit comprising an acceleration responsive switch of the mass-spring type having normally open contacts, and means for closing said contacts when said switch is subjected to a predetermined acceleration and reopening said contacts in the event said switch is closed in response to said predetermined acceleration and is subsequently subjected to an acceleration less than said predetermined acceleration, an electrical current-sensitive thermal relay, said relay comprising a housing, two spaced stationary contacts, a plunger adapted to bridge said contacts to complete an electrical circuit therebetween, spring means urging said plunger toward said bridging position, a fuse wire, means securing said fuse Wire to said plunger, and means securing said fuse wire to the housing of said relay, whereby said fuse wire is eifective to hold said plunger in a retracted position spaced from said stationary contacts, a rst source of potential, means interconnecting said rst source of potential, said fuse wire and said contacts of the acceleration switch in series connection, a second power source, means connecting said second power source in series with the normally open contacts of said relay and with a load device.

3. A missile arming and safety circuit comprising an acceleration responsive switch of the mass-spring type having normally open contacts, and means for closing said contacts when said switch is subjected to a predetermined acceleration and reopening said contacts in the event said switch is closed in response to said predetermined acceleration and is subsequently subjected to an acceleration less than said predetermined acceleration, an electrical current-sensitive thermal relay, said relay comprising a housing, two spaced stationary contacts, a plunger adapted to bridge said contacts to complete an electrical circuit therebetween, spring means urging said plunger toward said bridging position, a fuse wire, means securing said fuse wire to said plunger, and means securing said fuse wire to the housing of said relay, whereby said fuse wire is effective to hold said plunger in a retracted position spaced from said stationary contacts, a first source of potential, a resistor, means interconnecting said first source of potential, said resistor, said fuse wire and said contacts of the acceleration switch in series connection, a second power source, means connecting said second power source in series with the normally open contacts of said relay and with a load device.

4. A missile arming and safety circuit for a missile including a programmer, said circuit comprising an acceleration responsive switch of the mass-spring type having normally open contacts, and means for closing said contacts when said switch is subjected to a predetermined acceleration and reopening said contacts in the event said switch is closed in response to said predetermined acceleration and is subsequently subjected to an acceleration less than said predetermined acceleration, an electrical current-sensitive thermal relay, said relay comprising a housing, two spaced stationary contacts, a plunger adapted to bridge said contacts to complete an electrical circuit therebetween, spring means urging said plunger toward said bridging position, a fuse wire, means securing said fuse wire to said plunger, and means securing said fuse wire to the housing of said relay, whereby said fuse wire is effective to hold said plunger in a retracted position spaced from said stationary contacts, a rst source of potential, a resistor means interconnecting said iirst source of potential, said resistor, said fuse wire and said contacts of the acceleration switch in series connection, a second power source, means connecting said second power source in series with the normally open contacts of said relay and said programmer.

5. A missile arming and safety circuit for a missile including a programmer, said circuit comprising an acceleration responsive switch of the mass-spring type having normally open contacts, and means for closing said contacts when said switch is subjected to a predetermined acceleration and reopening said contacts in the event said switch is closed in response to said predetermined acceleration and is subsequently subjected to an acceleration less than said predetermined acceleration, an electrical current-sensitive thermal relay, said relay comprising two spaced stationary contacts, a plunger adapted to bridge said contacts to complete an electrical circuit therebetween, spring means urging said plunger toward said bridging position, a fuse wire, means securing said fuse wire to said plunger, and means securing said fuse wire to the housing of said relay, whereby said fuse wire is effective to hold said plunger in a retracted position spaced from said stationary contacts, a rst source of potential, a resistor means interconnecting said first source of potential, said resistor, said fuse wire and said contacts of the acceleration switch in series connectiona second power` source, means connecting said second power source in series with the normally open contacts of said relay and said programmer, whereby said fuse element melts to release said plunger and energize said programmer only after said acceleration responsive switch is closed for a predetermined time.

References Cited in the le of this patent UNITED STATES PATENTS 2,485,817 Dike Oct. 25, 1949 2,486,362 OBrien Oct. 25, 1949 2,498,040 Jordan et al Feb. 21, 1950 2,948,219 Sapp Aug. 9, 1960 3,039,363 Grillo et al June 19, 1962

Claims (1)

1. A MISSILE SAFETY AND ARMING CIRCUIT FOR A MISSILE INCLUDING A PROGRAMMER, SAID CIRCUIT COMPRISING AN ACCELERATION RESPONSIVE SWITCH OF THE MASS-SPRING TYPE HAVING NORMALLY OPEN CONTACTS AND INCLUDING MEANS FOR CLOSING SAID CONTACTS WHEN SAID SWITCH IS SUBJECTED TO A PREDETERMINED ACCELERATION AND REOPENING SAID CONTACTS IN THE EVENT SAID SWITCH IS CLOSED IN RESPONSE TO SAID PREDETERMINED ACCELERATION AND IS SUBSEQUENTLY SUBJECTED TO AN ACCELERATION LESS THAN SAID PREDETERMINED ACCELEARTION, AN ELECTRICAL CURRENT-SENSITIVE THERMAL RELAY HAVING A FUST ELEMENT, A FIRST SOURCE OF POTENTIAL, SAID RESISTOR, SAID CONNECTING SAID FIRST SOURCE OF POTENTIAL, SAID RESISTOR, SAID ACCELERATION SWITCH CONTACTS, AND SAID FUSE ELEMENT OF SAID RELAY IN SERIES ELECTRICAL CONNECTION, SAID RELAY HAVING A PAIR OF NORMALLY OPEN CONTACTS, A POWER SOURCE IN SERIES ELECTRICAL CONNECTION WITH SAID RELAY CONTACTS, AND MEANS INTERCONNECTING SAID POWER SOURCE AND SAID RELAY CONTACTS WITH SAID PROGRAMMER, WHEREBY SAID FUSE ELEMENT MELTS TO ENERGIZE SAID PROGRAMMER ONLY AFTER SAID ACCELERATION RESPONSIVE SWITCH IS CLOSED FOR A PREDETERMINED TIME.
US180533A 1962-03-19 1962-03-19 Missile safety and arming circuit Expired - Lifetime US3167018A (en)

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Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3323458A (en) * 1964-08-24 1967-06-06 Jr Henry W Hartmann Thermal fuze
US3453406A (en) * 1967-09-08 1969-07-01 Umc Ind Impact arming and tamper switch
US3475572A (en) * 1968-03-05 1969-10-28 Gen Electric Acceleration actuated switch with explosive charge and thermitic material
US3599572A (en) * 1969-10-22 1971-08-17 Avco Corp Safing and arming system for a munition
DE2133684A1 (en) * 1970-07-17 1972-01-20
US3745925A (en) * 1971-06-22 1973-07-17 S Hester Temperature and voltage controlled circuit
US4738201A (en) * 1985-10-31 1988-04-19 Holt Alan W Control devices
EP0341067A2 (en) * 1988-05-04 1989-11-08 British Aerospace Public Limited Company Universal artillery fuze
DE10354012A1 (en) * 2003-04-26 2004-11-18 Rheinmetall W & M Gmbh Gas pressure switch for an ignition and safety device for ammunition
US20050188877A1 (en) * 2003-04-26 2005-09-01 Rheinmetall W & M Gmbh Gas pressure switch
US10330225B2 (en) * 2017-01-28 2019-06-25 Mark Eugene Goodson Lightning resistant gas tubing system

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2486362A (en) * 1946-11-07 1949-10-25 Us Sec War Acceleration switch
US2485817A (en) * 1943-04-16 1949-10-25 Us Navy Detonator safety device
US2498040A (en) * 1943-05-05 1950-02-21 James D Jerdan Setback switch
US2948219A (en) * 1953-03-12 1960-08-09 Winfred F Sapp Rocket fuze
US3039363A (en) * 1960-01-28 1962-06-19 Salvatore J Grillo Rocket firing relay

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2485817A (en) * 1943-04-16 1949-10-25 Us Navy Detonator safety device
US2498040A (en) * 1943-05-05 1950-02-21 James D Jerdan Setback switch
US2486362A (en) * 1946-11-07 1949-10-25 Us Sec War Acceleration switch
US2948219A (en) * 1953-03-12 1960-08-09 Winfred F Sapp Rocket fuze
US3039363A (en) * 1960-01-28 1962-06-19 Salvatore J Grillo Rocket firing relay

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3323458A (en) * 1964-08-24 1967-06-06 Jr Henry W Hartmann Thermal fuze
US3453406A (en) * 1967-09-08 1969-07-01 Umc Ind Impact arming and tamper switch
US3475572A (en) * 1968-03-05 1969-10-28 Gen Electric Acceleration actuated switch with explosive charge and thermitic material
US3599572A (en) * 1969-10-22 1971-08-17 Avco Corp Safing and arming system for a munition
US3750588A (en) * 1970-07-17 1973-08-07 Philips Corp Arrangement in an electrical fuse for projectiles
DE2133684A1 (en) * 1970-07-17 1972-01-20
US3745925A (en) * 1971-06-22 1973-07-17 S Hester Temperature and voltage controlled circuit
US4738201A (en) * 1985-10-31 1988-04-19 Holt Alan W Control devices
EP0341067A3 (en) * 1988-05-04 1990-08-29 British Aerospace Public Limited Company Universal artillery fuze
EP0341067A2 (en) * 1988-05-04 1989-11-08 British Aerospace Public Limited Company Universal artillery fuze
DE10354012A1 (en) * 2003-04-26 2004-11-18 Rheinmetall W & M Gmbh Gas pressure switch for an ignition and safety device for ammunition
DE10354012B4 (en) * 2003-04-26 2005-06-30 Rheinmetall W & M Gmbh Gas pressure switch for an ignition and safety device of ammunition
US20050188877A1 (en) * 2003-04-26 2005-09-01 Rheinmetall W & M Gmbh Gas pressure switch
US7150228B2 (en) 2003-04-26 2006-12-19 Rheinmetall W & M Gmbh Gas pressure switch
US10330225B2 (en) * 2017-01-28 2019-06-25 Mark Eugene Goodson Lightning resistant gas tubing system
US20190249802A1 (en) * 2017-01-28 2019-08-15 Mark Eugene Goodson Dissipative lightning resistant tubing system
US10502345B2 (en) * 2017-01-28 2019-12-10 Mark Eugene Goodson Dissipative lightning resistant tubing system

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